CN106697281A - Variable-pitch rotor wing power system module - Google Patents
Variable-pitch rotor wing power system module Download PDFInfo
- Publication number
- CN106697281A CN106697281A CN201710139027.2A CN201710139027A CN106697281A CN 106697281 A CN106697281 A CN 106697281A CN 201710139027 A CN201710139027 A CN 201710139027A CN 106697281 A CN106697281 A CN 106697281A
- Authority
- CN
- China
- Prior art keywords
- variable
- displacement rotor
- pitch
- engine
- power system
- 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.)
- Pending
Links
- 239000007858 starting material Substances 0.000 claims abstract description 25
- 230000007246 mechanism Effects 0.000 claims abstract description 22
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 10
- 230000008878 coupling Effects 0.000 claims abstract description 10
- 238000010168 coupling process Methods 0.000 claims abstract description 10
- 238000005859 coupling reaction Methods 0.000 claims abstract description 10
- 238000006073 displacement reaction Methods 0.000 claims description 47
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 239000002131 composite material Substances 0.000 claims description 2
- 239000000835 fiber Substances 0.000 claims description 2
- 238000001816 cooling Methods 0.000 abstract description 5
- 230000005540 biological transmission Effects 0.000 description 7
- 238000010276 construction Methods 0.000 description 6
- 230000008859 change Effects 0.000 description 5
- 239000000446 fuel Substances 0.000 description 4
- 239000003921 oil Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000003213 activating effect Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
-
- B64D27/40—
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
Abstract
A variable-pitch rotor wing power system module is a relatively independent rotor wing power system. The variable-pitch rotor wing power system module comprises a variable-pitch rotor wing power assembly (1), a pitch variation control mechanism (2) and variable-pitch rotor wings (3). The variable-pitch rotor wing power assembly (1) comprises a machine frame (4), an engine (11), a speed reducer (14), a cooling fan (15), a starter (16), a clutch (12) and a coupling (13), wherein the engine (11), the speed reducer (14), the cooling fan (15) and the starter (16) are mounted on the machine frame (4). The machine frame (4) comprises an end plate (41), side plates (42), an engine support (43), a speed reducer support (44), a cooling fan support (45) and a starter support (46). The pitch variation control mechanism (2) comprises a pitch variation control rudder (21), a pitch variation rocker arm (22), a fixed disc (23) and a movable disc (24). Each variable-pitch rotor wing (3) comprises a rotor wing blade (31) and a propeller hub (32). The variable-pitch rotor wing power system module is compact in structure, can be used for driving the rotor wings and realizing variable-pitch control; and meanwhile, the variable-pitch rotor wing power system module is independent of a vehicle body structure of an unmanned aerial vehicle, and is suitable for layout of various aircrafts.
Description
Technical field
The present invention relates to the displacement rotor power system of aircraft, belong to aeronautical product technical field.
Background technology
Rotor system is the important component of modern helicopters and multi-rotor aerocraft.Spacing rotor system and displacement revolve
Wing system is the topmost two kinds of rotor systems of current small aircraft, and spacing rotor is to change rotation by changing variable rotor speed
Wing pulling force, and displacement oar is then by changing rotor away from completing.As contemporary aircraft is wanted to rotor power system
Raising is asked, displacement rotor power system increasingly obtains the favor of Flight Vehicle Design personnel, and this key factor is two aspect reasons：
1 is limited in scope with the increase of paddle size, rotor inertia increase, the rotation speed change of spacing oar；2 displacement rotor power systems are led to
Crossing change pitch has dynamic response speed higher.But, compared to spacing rotor system, displacement rotor system increased change
Spacing mechanism, its structure is also relative complex, which not only improves the difficulty of its system structure design in itself, also complete machine structure is designed
Propose requirement higher.The present invention relates to a kind of displacement rotor system power plant module, the power plant module is integrated with fuel oil and starts
Machine and its power assembly, starter, radiator fan and rotor pitch-changing mechanism, simplify the structure cloth of the dynamic displacement rotor system of oil
Office, makes many rotor power parts of displacement independently of overall aircraft frame structure, is not changing drive system mode and inside portion
In the case of part relative position, various aircraft body structures are applicable, including many rotors, tiltrotor aircraft etc..
The content of the invention
The present invention relates to a kind of displacement rotor power system module, the rotor power system module compact conformation can drive
Dynamic rotor simultaneously realizes variable pitch contro l, is controlled by the mixing to throttle and pitch, reaches the lift requirement specified, and improves power
The liter force response rate of system.
The invention provides a kind of displacement rotor power system module, including displacement rotor power assembly (1), variable pitch contro l
Mechanism (2) and displacement rotor (3).
The displacement rotor power assembly (1), including frame (4), are installed on engine (11), clutch in frame (4)
Device (12), shaft coupling (13), decelerator (14), radiator fan (15) and starter (16).The radiator fan (15), starter
(16), the input of clutch (12), shaft coupling (13) and decelerator (14) is coaxial with engine (11).The power assembly collection
Into the function of starter, radiating, driving and displacement, various displacement rotors (three blade rotors, four blade rotors etc.) are adapted to.Engine
(11) power output is delivered to displacement rotor (3) via clutch (12), shaft coupling (13) and decelerator (14) successively, is flight
Device provides lift；Clutch (12) ensures that engine starts from car, closes car operating.Decelerator (14) can effectively improve power assembly
Output torque, to adapt to the rated operation of displacement rotor (3).Radiator fan (15) can realize cooling engine (11)
Function.Starter (16) provides power for engine start.
The frame (4) includes end plate, two side plates (42) perpendicular to end plate (41) plane, and between biside plate
Multiple equipment support (engine support (43), reducer stent (44), support of radiating fan (45) and starter support (46)),
Described equipment supporter is used to fix the engine (11), decelerator (14), radiator fan (15) and starter (16).Its
In, engine support (43) and starter support (46) plane are both perpendicular to end plate (41) and side plate (42) plane.The machine
Each part is plate stem structure type in frame (4), it is adaptable to carbon fibre composite moulding process, processes and low cost of manufacture,
Each part of structure is easy to dismounting simultaneously, and the connecting interface with aircraft body structure is laid out suitable for various aircraft.
The variable pitch contro l mechanism (2), including variable pitch contro l steering wheel (21), distance-variable rocker arm (22), price fixing (23) and Moving plate
(24).The pitch-changing mechanism is that it is remained always away from pitch-changing mechanism with the difference of conventional helicopters pitch-changing mechanism, eliminates the cycle
It is simple and compact for structure away from pitch-changing mechanism, reliability enhancing.Steering wheel (21) provides driving force, distance-variable rocker arm (22) for pitch-changing mechanism
Price fixing (23) and Moving plate (24) is driven to be moved along engine output shaft direction, while price fixing (23) is produced along deceleration with Moving plate (24)
Device output shaft is rotated against, realize rotary wing changing away from spinfunction.Variable pitch contro l mechanism (2) all actuation mechanisms and driving
Part is installed in inside modules, does not exist mechanical interface between aircraft body structure.
The displacement rotor (3), including rotor blade (31) and propeller hub (32).The displacement rotor and conventional helicopters rotor
Identical, three leaf oars, four leaf oars and leafy oar are applicable.
Technical characterstic of the invention is：
1. the design of power assembly of the present invention is compacter, all drive apparatus (radiator fan, starter, shaft coupling,
Clutch, decelerator input) it is coaxial with engine shaft, the flexible coupling of use can effectively vibration isolation, and transmission efficiency.
And at present applied or patent of invention ([CN201510352516], [CN201510834969], [CN201510708147),
[CN201410790940]) described in many rotor power systems be by belt or Bevel Gear Transmission, this mode
Transmission efficiency can be lost, and corresponding supporting construction is also complicated, and engine support is located inside aircraft body, rotor system
The structure design for influencing whether whole machine is changed in design, and scalability is not high；
2. structure design of the present invention uses drawer-type structure, side plate to surround semi-closed structure, drive apparatus support with end plate
Can be based on side plate, between biside plate, this structure type is conducive to the extension of drive apparatus and reduces, and can
Directly by support unit load transmission to end plate, Path of Force Transfer is relatively direct, structural bearing efficiency high.
The solution have the advantages that：
1. coaxial transmission design is carried out by above-mentioned each part of rotor power assembly and special knot is carried out to driving frame
Structure is designed so that the power section of many rotors of displacement forms independent system module independently of rack construction, is not changing system
In the case of the kind of drive and internal part relative position, it is adaptable to the housing construction of various unmanned planes.
2. on power assembly equipment removal with extend it is relatively easy, only need to be added in the drive path of power assembly or
Removing device, and attachment structure is designed on the correspondence position of assembly rack construction, improve displacement rotor power assembly
The flexibility of function.
Brief description of the drawings
Fig. 1 is displacement rotor power system module schematic diagram of the present invention；
Fig. 2 is power assembly schematic diagram of the present invention；
Fig. 3 is rack construction schematic diagram of the present invention；
Fig. 4 is variable pitch contro l structural representation of the present invention；
In figure：
Specific embodiment
Below in conjunction with accompanying drawing, the invention will be further described.
The dynamic displacement rotor power system module of oil of the invention can drive rotor and realize variable pitch contro l, by throttle and
The mixing control of pitch, reaches the lift requirement specified.Preferably, its controller should carry out lift control by changing pitch,
Throttle is compensated automatically simultaneously, to ensure the stability that lift is exported.
Displacement rotor power system module, including the rotation of displacement rotor power assembly (1), variable pitch contro l mechanism (2) and displacement
The wing (3), referring to Fig. 1.
Fig. 2 shows the embodiment of displacement rotor power assembly (1), including frame (4), is installed on the combustion in frame (4)
Oil turbine (11), centrifugal clutch (12), diaphragm coupling (13), parallel shaft (speed) reducer (14), radiator fan (15) and
Starter (16).Such as Fig. 2, described radiator fan (13), starter (14), centrifugal clutch (15), diaphragm coupling
(16) and parallel shaft (speed) reducer (12) input it is coaxial with fuel engines (11).
Described engine (11) as displacement rotor (3) driving force main source, four strokes, two stroke engine are equal
It is applicable, it should provide enough running powers to drive rotor.Preferably, clutch (12) is centrifugal clutch, structure letter
It is single, and the slow-speed of revolution can be realized from car, rotating speed high closes car function, it is ensured that engine starts from car, closes car operating.Preferably, join
Axle device (13) is diaphragm type coupler, and it can adapt to clutch (12) output shaft and is installed with the decentraction of decelerator (14) input shaft
Produced eccentric error.Decelerator (14) should effectively improve the output torque of power assembly, to take into account displacement rotor (3) and combustion
The rated operation of oil turbine (11), improves fuel utilization ratio, and decelerator uses parallel gears decelerator in the present embodiment,
The retarder variants such as parallel gears, bevel gear, planetary gear are not limited to herein to be applicable.Radiator fan (15) should be connected directly between
On engine output shaft, radiator fan (15) is directly driven using the power of fuel engines (11), to strengthen local wind rate, from
And the purpose for cooling down fuel engines (11) is reached, radiator fan should have wind guide component, directly increase engine cylinder-body fin
Partial local air flow.Starter (16) should be connected directly between on engine output shaft, by its motor internal and deceleration
Device drives engine to reach toggle speed and provide enough starting torques, general to require, when electrically activating maximum power operation
Engine can reach more than initial velocity 500rpm, meanwhile, electrically activating should install unilateral bearing between engine shaft, to protect
Power assembly runs well after card starts.
Fig. 3 shows the embodiment of the frame (4) structure one, including end plate, two sides perpendicular to end plate (41) plane
Plate (42), and multiple equipment support (engine support (43), reducer stent (44), radiator fan branch between biside plate
Frame (45) and starter support (46)), described equipment supporter is used to fix the engine (11), decelerator (12), radiating
Fan (13) and starter (14).Wherein, engine support (43) and starter support (46) plane are both perpendicular to end plate
And side plate (42) plane (41).Such as Fig. 3, frame end plate (41) is joined directly together as each support is carried with biside plate (42) in the embodiment
For basis, the space between biside plate (42) is from bottom to top successively with bolt connection engine support (43), support of radiating fan
(45), starter support (46) and reducer stent (44).Preferably, engine support (43) should be installed and engine between and subtracted
Shake pad, is fixed in engine connecting bracket by engine connecting bolt.Starter support (45) is according to starter form
It is designed, it is preferred that between biside plate (42).Preferably, decelerator (46) support mounting point is defeated positioned at decelerator
Shaft lower section, directly by rotor load transmission to rack construction, with optimizing load transfer path, to reduce the load of reducer shell
Lotus.
Fig. 4 shows the embodiment of variable pitch contro l mechanism (2), including variable pitch contro l steering wheel (21), and distance-variable rocker arm (22) is fixed
Disk (23) and Moving plate (24).The present embodiment pitch-changing mechanism provides drive using single rocking arm type of drive, steering wheel (21) for pitch-changing mechanism
Power, distance-variable rocker arm (22) drives price fixing (23) and Moving plate (24) to be moved along engine output shaft direction, price fixing (23) and Moving plate
(24) relatively rotated between, sliding bearing, price fixing (23) and Moving plate should be installed between price fixing (23) and decelerator (14) output shaft
(24) deep groove ball bearing or needle bearing should be installed between.Such as Fig. 4, variable pitch contro l mechanism (2) all actuation mechanisms and drive division
Part is installed in inside modules, does not exist mechanical interface between aircraft body structure.
Core of the invention is to carry out coaxial transmission to each part of power assembly of many rotors of displacement to design and for total
Special structure design is carried out into frame, displacement rotor power system itself is formd independent system module, extend change
Away from the rotor power system scope of application on board the aircraft, six are extended in the case of being designed internal system is not changed
In many rotor-hub configurations such as rotor, eight rotors.The present invention is not limited to above-mentioned specific embodiment, if various changed to of the invention
Dynamic and deformation does not depart from the scope of the invention, within the scope of still falling within claim of the invention and equivalent technology.
Claims (10)
1. a kind of displacement rotor power assembly, including frame (4), is installed on engine (11), decelerator in frame (4)
(14), radiator fan (15) and starter (16), clutch (12) and shaft coupling (13), it is characterised in that the radiator fan,
The input of starter, shaft coupling, clutch and decelerator is coaxial with engine shaft.
2. displacement rotor power assembly as claimed in claim 1, it is characterised in that the frame includes end plate and perpendicular to end
Two side plates of plate plane.
3. displacement rotor power assembly as claimed in claim 2, it is characterised in that be provided with multiple between described two side plates
Support, the support is used to fix the engine, decelerator, radiator fan and starter.
4. displacement rotor power assembly as claimed in claim 3, it is characterised in that the frame includes engine support
(43), its plane is both perpendicular to the end plate and side plate planar.
5. displacement rotor power assembly as claimed in claim 3, it is characterised in that the frame includes starter support
(46), its plane is both perpendicular to the end plate and side plate planar.
6. displacement rotor power assembly as claimed in claim 1, it is characterised in that the frame is by carbon fibre composite system
Into.
7. a kind of displacement rotor power system module, it is characterised in that total including displacement rotor power as claimed in claim 1
Into (1), variable pitch contro l mechanism (2) and displacement rotor (3).
8. displacement rotor power system module as claimed in claim 7, it is characterised in that variable pitch contro l mechanism (2) bag
Variable pitch contro l steering wheel (21), distance-variable rocker arm (22), price fixing (23) and Moving plate (24) are included, the steering wheel (21) provides driving force, institute
Stating distance-variable rocker arm (22) drives the price fixing (23) and the Moving plate (24) to be moved along engine output shaft direction, while described fixed
Disk (23) and the Moving plate (24) produce rotating against along reducer output shaft, realize rotary wing changing away from spinfunction,
Do not exist mechanical interface between the variable pitch contro l mechanism (2) and aircraft body structure.
9. displacement rotor power system module as claimed in claim 7, it is characterised in that the displacement rotor (3) includes rotation
Wing blade (31) and propeller hub (32).
10. displacement rotor power system module as claimed in claim 7, it is characterised in that the displacement rotor (3) is including three
Leaf oar, four leaf oars or more leaf oar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710139027.2A CN106697281A (en) | 2017-03-09 | 2017-03-09 | Variable-pitch rotor wing power system module |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710139027.2A CN106697281A (en) | 2017-03-09 | 2017-03-09 | Variable-pitch rotor wing power system module |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106697281A true CN106697281A (en) | 2017-05-24 |
Family
ID=58912254
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710139027.2A Pending CN106697281A (en) | 2017-03-09 | 2017-03-09 | Variable-pitch rotor wing power system module |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106697281A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110228587A (en) * | 2019-07-03 | 2019-09-13 | 中国人民解放军国防科技大学 | Pitch-varying system and unmanned aerial vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110139939A1 (en) * | 2008-06-27 | 2011-06-16 | Glenn Neil Martin | Personal flight device incorporating radiator cooling passage |
| WO2012010021A1 (en) * | 2010-07-19 | 2012-01-26 | Yang zhaoxi | Air-ground double-purpose aircraft |
| CN104369862A (en) * | 2014-10-27 | 2015-02-25 | 湖南农业大学 | Pilotless helicopter |
| CN205060011U (en) * | 2015-10-27 | 2016-03-02 | 中航维拓（北京）科技有限责任公司 | Oil moves four rotor unmanned aerial vehicle rotor - control system of displacement |
| CN205087141U (en) * | 2015-11-04 | 2016-03-16 | 中航维拓（北京）科技有限责任公司 | Oil moves coaxial rotor - control system of six coaxial rotor unmanned aerial vehicle of displacement |
| CN206552264U (en) * | 2017-03-09 | 2017-10-13 | 北京天宇新超航空科技有限公司 | A kind of displacement rotor power system module |
-
2017
- 2017-03-09 CN CN201710139027.2A patent/CN106697281A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110139939A1 (en) * | 2008-06-27 | 2011-06-16 | Glenn Neil Martin | Personal flight device incorporating radiator cooling passage |
| WO2012010021A1 (en) * | 2010-07-19 | 2012-01-26 | Yang zhaoxi | Air-ground double-purpose aircraft |
| CN104369862A (en) * | 2014-10-27 | 2015-02-25 | 湖南农业大学 | Pilotless helicopter |
| CN205060011U (en) * | 2015-10-27 | 2016-03-02 | 中航维拓（北京）科技有限责任公司 | Oil moves four rotor unmanned aerial vehicle rotor - control system of displacement |
| CN205087141U (en) * | 2015-11-04 | 2016-03-16 | 中航维拓（北京）科技有限责任公司 | Oil moves coaxial rotor - control system of six coaxial rotor unmanned aerial vehicle of displacement |
| CN206552264U (en) * | 2017-03-09 | 2017-10-13 | 北京天宇新超航空科技有限公司 | A kind of displacement rotor power system module |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110228587A (en) * | 2019-07-03 | 2019-09-13 | 中国人民解放军国防科技大学 | Pitch-varying system and unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2458826C2 (en) | Perfecting rotorcraft equipped with gas turbine engine | |
| US8562284B2 (en) | Propulsive fan system | |
| US20130147204A1 (en) | Hybrid Drive And Energy System For Aircraft | |
| CN203428022U (en) | Electromagnetic variable-pitch propeller of unmanned aerial vehicle | |
| CN105270619B (en) | A kind of four rotor wing unmanned aerial vehicle of dynamic displacement of oil | |
| WO2019154067A1 (en) | Active main rotor blade vertical take-off and landing aircraft | |
| WO2020190344A2 (en) | Architectures for hybrid-electric propulsion | |
| WO2019154064A1 (en) | Gasoline-electric hybrid power vertical take-off and landing aircraft having driving rotors | |
| EP3876400B1 (en) | Electric drive system line replaceable unit with integrated thermal cooling | |
| CN108082499A (en) | Planetary hybrid power helicopter dynamic coupling system and driving method | |
| US8297039B2 (en) | Propulsion engine | |
| CN106741904A (en) | A kind of compound unmanned vehicle | |
| CN206552264U (en) | A kind of displacement rotor power system module | |
| CN207466966U (en) | A kind of dynamic displacement quadrotor unmanned plane of oil | |
| CN106697281A (en) | Variable-pitch rotor wing power system module | |
| CN206494122U (en) | Aircraft power mechanism and multi-rotor unmanned aerial vehicle | |
| CN209776795U (en) | Unmanned aerial vehicle and horn system thereof | |
| CN208007286U (en) | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer | |
| CN1335248A (en) | Helicopter with driving rotary wings | |
| WO2009143669A1 (en) | Aircraft and the power driving system thereof | |
| CN206871351U (en) | A kind of compound unmanned vehicle | |
| CN2434226Y (en) | Active rotary wing helicopter | |
| CN113710575A (en) | Drive, in particular for the main rotor of a rotary-wing aircraft | |
| CN213948754U (en) | Ducted fan | |
| CN103803065A (en) | Belt-transmission disc type multi-rotor-wing aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170524 |
|
| WD01 | Invention patent application deemed withdrawn after publication |