CN108750099A - A kind of band is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing - Google Patents
A kind of band is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing Download PDFInfo
- Publication number
- CN108750099A CN108750099A CN201810551573.1A CN201810551573A CN108750099A CN 108750099 A CN108750099 A CN 108750099A CN 201810551573 A CN201810551573 A CN 201810551573A CN 108750099 A CN108750099 A CN 108750099A
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- wing
- compound
- lift
- auxiliary wing
- aircraft
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Classifications
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- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/54—Varying in area
- B64C3/546—Varying in area by foldable elements
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention is a kind of hybrid lift aircraft of band expansion platform, by rear single-screw paddle composite wing aircraft and is assemblied in being formed without the compound auxiliary wing of thrust self energizing for its both sides；Wherein, rear single-screw paddle composite wing aircraft include body, it is foldable be mounted on body both sides hybrid lift wing, screw propeller；Wherein, body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, hybrid lift wing outside are designed with wing hinge；Self-enclosed ducted fan is provided in the no compound auxiliary wing of thrust self energizing, the one or both sides of the no compound auxiliary wing of thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and are flexibly connected with hybrid lift wing by wing hinge.The present invention not only has landing apart from short, flying speed is fast, wing structure intensity is high, wing can with energy storage, low energy consumption for flight, the hang time is long, safe the features such as.
Description
Technical field
The present invention relates to a kind of aircraft, specifically a kind of band is compound without the rear single screw folding for pushing away the compound auxiliary wing
Rotor aircraft belongs to aircraft equipment technology field.
Background technology
Existing aircraft is broadly divided into fixed-wing and vertically taking off and landing flyer（Such as helicopter and more rotors）Two major classes.When
So also there is this product of VTOL fixed-wing.Traditional fixed-wing have the advantages that flying speed is fast, low energy consumption, but have
It is not connected to before and after main wing and tailplane, wing structure intensity is not high, is easily damaged, and landing requires high, landing distance disadvantage；
Traditional vertically taking off and landing flyer has the advantages that landing is convenient, but has that energy consumption is big, safety coefficient is low, and load capacity is poor, water
Flat flying speed is slow, is easy the shortcomings of air crash；Although current VTOL fixed-wing has the characteristics that landing is convenient, but in water
The shortcomings of controllability when flat flight is not satisfactory, and that there is flight resistances is big, and energy consumption is high, and safety coefficient is not still high.
Invention content
In view of the above-mentioned problems of the prior art, the present invention not only has landing apart from short, flying speed is fast, wing knot
Structure intensity height, wing can be with energy storage, the features such as low energy consumption, the hang time is long of flying, the hybrid lift wing of large area, feelings of meeting an urgent need
It can play the role of aerodone under condition, greatly improve the safety of aircraft, the safety of support personnel.
To achieve the goals above, the present invention includes rear single-screw paddle composite wing aircraft, is movably arranged on compound liter
Power aircraft both sides without the compound auxiliary wing of thrust self energizing；Wherein, rear single-screw paddle composite wing aircraft includes body, can roll over
It is folded to be mounted on body both sides hybrid lift wing, screw propeller；Wherein, body is set as deck platform；Hybrid lift machine
Self-enclosed ducted fan built in the wing, hybrid lift wing outside are designed with wing hinge；It is set in the no compound auxiliary wing of thrust self energizing
It is equipped with self-enclosed ducted fan, the one or both sides of the no compound auxiliary wing of thrust self energizing are provided with electro-hydraulic gas interface and wing hinge
Chain, and be flexibly connected with hybrid lift wing by wing hinge.Cockpit is mounted on the lower section of body.
Further, hybrid lift wing is mounted on body both sides by the way that folding hinge is folding.
Further, propeller is a variety of dynamic structures such as electric propeller, the dynamic propeller of oil.
Further, hybrid lift wing can be divided into two parts of lift main wing and balance empennage, be separately positioned on compound
The front and back of lifting wing；It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space；Its
In, at least there are one self-enclosed ducted fans for installation inside lift main wing.
Further, further include vertical tail, the vertical tail is arranged above or below body；The vertical tail is set
It sets in wing both sides；The vertical tail may be implemented to fold；Mobilizable vertical rudder wing is installed behind the vertical tail.
Further, body is set as deck platform；The mounting hole of the regular arrangement in deck platform both sides；The first
It is designed with socket on plate platform；The socket is female or male.
Further, electro-hydraulic gas interface carries lid.
Further, the compound auxiliary wing of no thrust self energizing can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance, respectively
It is arranged in the front and back of the compound auxiliary wing of no thrust self energizing；Space is reserved between the auxiliary wing of lift and the auxiliary empennage of balance, in space
It is provided with the horizontal lifting rudder wing；Wherein, at least there are one self-enclosed ducted fans for installation inside the auxiliary wing of lift.
Further, engine installation position, engine installation position are additionally provided on the compound auxiliary wing of no thrust self energizing（111）It is interior
It is provided with power plant.
Further, it is provided with battery/fuel on the compound auxiliary wing of no thrust self energizing.
The prior art is compared, the main feature having is invented：
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, wing
It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight
Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2, foldable pattern is used between body and both sides wing；Fold mechanism is folding hinge；After the wing expansion of both sides
It can locking.Occupied space when to reduce storage and transport is particularly suitable under the limited environment in the spaces such as family and aircraft carrier
It uses.Using the program, the quantity of the carrier-borne aircraft of aircraft carrier can be greatly improved.The hangar of same area, can store double
The aircraft of quantity；Or realize the advantages that quantity for the aircraft that medium-sized aircraft carrier carries is no less than large-scale aircraft carrier.
3, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated
Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously
The safety of row device has ensured the safety of personnel and goods and materials.
4, the present invention can realize multiple functions using hardware and software platform, modularized design,
5, the present invention using both sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
6, the present invention also has successive socket, and the cluster of aircraft is facilitated to fly, and further decreases cluster flight
When power consumption.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, can be achieved with flying for long range
Row, not the cluster flight of only aircraft provide the low-power consumption scheme of clustering, it might even be possible to realize the sky between aircraft
Middle rescue, i.e., before aircraft the dragging of faulty aircraft below is taken off, realize and mutually come to sb.'s rescue between aircraft not seen before
Help phenomenon.
7. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable input of client, reduces buying and operation cost.
8. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the present invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, it is synchronous to be controlled by hybrid lift aircraft main control unit, it expands again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
9. thrust device modularization can very easily realize that repair is replaced.
In 11 present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift aircraft
Energy intercommunication between main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
12. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
13. aerofoil type energy device, efficiently uses space.
14. the present invention uses modularized design, compound different types of machines to use, cost has been saved.
Description of the drawings
Fig. 1 is the structural schematic diagram of the present invention；
Fig. 2 is the side view of the present invention；
Fig. 3 is the rearview of the present invention；
Fig. 4 is the plan view of the present invention；
Fig. 5 is the oblique view of the present invention；
In figure：101：Body；102：Hybrid lift wing；104：Self-enclosed ducted fan；105：Vertical tail；1051. vertical
The rudder wing；106：Propeller；107：Energy Management System；1021：Lift main wing；1022：The horizontal lifting rudder wing；1023：Balance tail
The wing；1028：Wing hinge；1001：Socket；1002：Cavity；1003：Mounting hole；1006：Battery/fuel；108：Video camera；
1026：Convex series connection head；1027：Spill series connection seat；1031, without the compound auxiliary wing of thrust self energizing；10311, the auxiliary wing of lift；
10312, auxiliary empennage is balanced；1026, electro-hydraulic gas interface；10261, lid；111, engine installation position；1059：Folding hinge.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
As shown in Figures 1 to 5, a kind of band is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing, packet
Include rear single-screw paddle composite wing aircraft, be movably arranged on hybrid lift aircraft both sides without the compound auxiliary wing of thrust self energizing
1031 compositions；111, engine installation position.
Wherein, the rear single-screw paddle composite wing aircraft include body 101, it is foldable be mounted on 101 liang of body
Side hybrid lift wing 102, propeller 106；Wherein, the body 101 is set as deck platform；The hybrid lift machine
Self-enclosed ducted fan 104 built in the wing 102,102 outside of hybrid lift wing are designed with wing hinge 1028；
It is described without self-enclosed ducted fan 104 is provided in the compound auxiliary wing of thrust self energizing 1031, no thrust self energizing is compound
The one or both sides of the auxiliary wing 1031 are provided with electro-hydraulic gas interface 1026 and wing hinge 1028, and by wing hinge 1028 and again
Lifting wing 102 is closed to be flexibly connected.
As further improvement of the invention, hybrid lift wing 102 is mounted on by the way that folding hinge 1059 is folding
101 both sides of body.
As further improvement of the invention, propeller 106 is the various ways such as electric propeller, the dynamic propeller of oil.
As further improvement of the invention, hybrid lift wing 102 can be divided into lift main wing 1021 and balance empennage
1023 two parts, are separately positioned on the front and back of hybrid lift wing 102；Between lift main wing 1021 and balance empennage 1023
It is reserved with space, the horizontal lifting rudder wing 1022 is provided in space；Wherein, at least there are one certainly for installation inside lift main wing 1021
Close ducted fan 104.
Improved as of the invention further, vertical tail 105, vertical tail 105 be arranged above body 101 or under
Side；The vertical tail 105 is arranged in wing both sides；The vertical tail 105 may be implemented to fold；The vertical tail 105
Mobilizable vertical rudder wing 1051 is installed below.
As further improvement of the invention, body 101 is set as deck platform；The deck platform both sides are regular
The mounting hole 1003 of arrangement；Socket 1001 is designed in the deck platform；The socket 1001 is female or male.
As further improvement of the invention, electro-hydraulic gas interface 1026 carries lid 10261.
Improved as of the invention further, can be divided into the auxiliary wing of lift 10311 without the compound auxiliary wing of thrust self energizing 1031
And auxiliary 10,312 two parts of empennage of balance, it is separately positioned on the front and back of the compound auxiliary wing of no thrust self energizing 1031；Lift is auxiliary
It is reserved with space between the wing 10311 and the auxiliary empennage of balance 10312, the horizontal lifting rudder wing 1022 is provided in space；Wherein, lift
At least there are one self-enclosed ducted fans 104 for installation inside the auxiliary wing 10311.
It is improved as of the invention further, engine installation position is additionally provided on the compound auxiliary wing of no thrust self energizing 1031
111, power plant is provided in engine installation position 111.
It is improved as of the invention further, battery/fuel 1006 is provided on the compound auxiliary wing of no thrust self energizing 1031.
The prior art is compared, the main feature having is invented：
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, wing
It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight
Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2. using foldable pattern between body and both sides wing；Fold mechanism is folding hinge；After the wing expansion of both sides
It can locking.Occupied space when to reduce storage and transport is particularly suitable under the limited environment in the spaces such as family and aircraft carrier
It uses.Using the program, the quantity of the carrier-borne aircraft of aircraft carrier can be greatly improved.The hangar of same area, can store double
The aircraft of quantity；Or realize the advantages that quantity for the aircraft that medium-sized aircraft carrier carries is no less than large-scale aircraft carrier.
3, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated
Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously
The safety of row device has ensured the safety of personnel and goods and materials.
4, the present invention can realize multiple functions using hardware and software platform, modularized design,
5, the present invention using both sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
6, the present invention also has successive socket, and the cluster of aircraft is facilitated to fly, and further decreases cluster flight
When power consumption.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, can be achieved with flying for long range
Row, not the cluster flight of only aircraft provide the low-power consumption scheme of clustering, it might even be possible to realize the sky between aircraft
Middle rescue, i.e., before aircraft the dragging of faulty aircraft below is taken off, realize and mutually come to sb.'s rescue between aircraft not seen before
Help phenomenon.
7. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable input of client, reduces buying and operation cost.
8. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the present invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, it is synchronous to be controlled by hybrid lift aircraft main control unit, it expands again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
9. thrust device modularization can very easily realize that repair is replaced.
10. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and fly with hybrid lift
Energy intercommunication between device main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
11. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
12. aerofoil type energy device, efficiently uses space.
13. the present invention uses modularized design, compound different types of machines to use, cost has been saved.
Schematically the present invention and embodiments thereof are described above, description is not limiting, institute in attached drawing
What is shown is also one of embodiments of the present invention, and actual structure is not limited to this.So if the common skill of this field
Art personnel are enlightened by it, without departing from the spirit of the invention, are not inventively designed and the technical solution
Similar frame mode and embodiment, are within the scope of protection of the invention.
Claims (10)
1. a kind of band is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing, which is characterized in that including rear list
The compound rotor aircraft of propeller type, be assemblied in its wing both sides without the compound auxiliary wing of thrust self energizing；
Wherein, the rear single-screw paddle composite wing aircraft includes body（101）, it is foldable be mounted on body（101）Two
The hybrid lift wing of side（102）, propeller（106）；Wherein, the body（101）It is set as deck platform；Described answers
Close lifting wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside is designed with wing hinge
(1028)；Propeller（106）For screw propeller；
It is described without being provided with self-enclosed ducted fan in the compound auxiliary wing of thrust self energizing（104）, no thrust self energizing is compound auxiliary
The one or both sides of the wing are provided with electro-hydraulic gas interface（1026）With wing hinge (1028), and by wing hinge (1028) with it is multiple
Close lifting wing（102）Flexible connection.
2. a kind of band according to claim 1 is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing,
It is characterized in that, the hybrid lift wing（102）Pass through folding hinge（1059）It is folding to be mounted on body（101）Two
Side.
3. a kind of band according to claim 1 is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing,
It is characterized in that, the propeller（106）For screw propeller；The propeller（106）It is dynamic for electric propeller, oil
A variety of dynamic structures such as propeller.
4. a kind of band according to claim 1 is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing,
It is characterized in that, the hybrid lift wing（102）Lift main wing can be divided into（1021）And balance empennage（1023）Two
Part is separately positioned on hybrid lift wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between it is pre-
There are space, the horizontal lifting rudder wing is provided in space（1022）；Wherein, lift main wing（1021）There are one internal at least installations
Self-enclosed ducted fan（104）.
5. a kind of band according to claim 1 is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing,
It is characterized in that, further including vertical tail（105）, the vertical tail（105）It is arranged in body（101）Above or below；Institute
State vertical tail（105）It is arranged in wing both sides；The vertical tail（105）It may be implemented to fold；The vertical tail（105）
Mobilizable vertical rudder wing is installed below（1051）.
6. a kind of band according to claim 1 is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing,
It is characterized in that, the body（101）It is set as deck platform；The mounting hole of the regular arrangement in deck platform both sides
（1003）；It is designed with socket in the deck platform（1001）；The socket（1001）For female or male.
7. a kind of band according to claim 1 is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing,
It is characterized in that, the electro-hydraulic gas interface（1026）With lid（10261）.
8. a kind of band according to claim 1 is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing,
It is characterized in that, the compound auxiliary wing of no thrust self energizing can be divided into the auxiliary wing of lift（10311）And the auxiliary empennage of balance
（10312）Two parts are separately positioned on the front and back of the compound auxiliary wing of no thrust self energizing；The auxiliary wing of lift（10311）With balance
Auxiliary empennage（10312）Between be reserved with space, the horizontal lifting rudder wing is provided in space（1022）；Wherein, the auxiliary wing of lift
（10311）There are one self-enclosed ducted fans for internal at least installation（104）.
9. a kind of band according to claim 1 is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing,
It is characterized in that, being additionally provided with engine installation position on the compound auxiliary wing of no thrust self energizing（111）, engine installation position
（111）Inside it is provided with power plant.
10. a kind of band according to claim 1 is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing,
It is characterized in that, being provided with battery/fuel on the compound auxiliary wing of no thrust self energizing（1006）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810551573.1A CN108750099A (en) | 2018-05-31 | 2018-05-31 | A kind of band is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810551573.1A CN108750099A (en) | 2018-05-31 | 2018-05-31 | A kind of band is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108750099A true CN108750099A (en) | 2018-11-06 |
Family
ID=64001317
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810551573.1A Pending CN108750099A (en) | 2018-05-31 | 2018-05-31 | A kind of band is without the rear compound rotor aircraft of single screw folding for pushing away the compound auxiliary wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108750099A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935512A (en) * | 2014-05-12 | 2014-07-23 | 马轶 | High endurable multi-rotor craft |
| CN205131644U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Four -axis glide vehicle |
| CN206871353U (en) * | 2017-05-16 | 2018-01-12 | 许育俊 | A kind of portable folding aircraft |
| CN107813929A (en) * | 2016-09-11 | 2018-03-20 | 郎风 | Combined type dalta wing duct aircraft |
-
2018
- 2018-05-31 CN CN201810551573.1A patent/CN108750099A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935512A (en) * | 2014-05-12 | 2014-07-23 | 马轶 | High endurable multi-rotor craft |
| CN205131644U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Four -axis glide vehicle |
| CN107813929A (en) * | 2016-09-11 | 2018-03-20 | 郎风 | Combined type dalta wing duct aircraft |
| CN206871353U (en) * | 2017-05-16 | 2018-01-12 | 许育俊 | A kind of portable folding aircraft |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181106 |
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| RJ01 | Rejection of invention patent application after publication |