CN108820201A - Rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust - Google Patents
Rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust Download PDFInfo
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- CN108820201A CN108820201A CN201810551068.7A CN201810551068A CN108820201A CN 108820201 A CN108820201 A CN 108820201A CN 201810551068 A CN201810551068 A CN 201810551068A CN 108820201 A CN108820201 A CN 108820201A
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- wing
- airscrew thrust
- compound auxiliary
- auxiliary wing
- compound
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- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The present invention is the rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust, is made of rear single-screw paddle composite wing aircraft and the compound auxiliary wing of airscrew thrust self energizing for being assemblied in its wing two sides；Single-screw paddle composite wing aircraft includes body, is fixedly mounted on body two sides hybrid lift wing, propeller afterwards；Body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, the outside design of hybrid lift wing have wing hinge；Propeller is screw propeller.The present invention not only has landing apart from short, flying speed is fast, wing structure intensity is high, wing can with energy storage, flight low energy consumption, the hang time is long the features such as, the auxiliary wing uses hybrid lift, ensure the adaptation range of power, the hybrid lift wing of large area simultaneously, it can play the role of aerodone under case of emergency, greatly improve the safety of aircraft, the safety of support personnel and goods and materials.
Description
Technical field
The present invention relates to a kind of aircraft, specifically a kind of rear single-screw paddle with the compound auxiliary wing of airscrew thrust is compound
Wing manned vehicle belongs to aircraft equipment technology field.
Background technique
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 high, safety coefficient is low, and load capacity is poor, water
Flat flying speed is slow, is easy the disadvantages of air crash；Although current VTOL fixed-wing has the characteristics that landing is convenient, but in water
The disadvantages 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.
Summary of the invention
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 and goods and materials.
To achieve the goals above, the present invention by rear single-screw paddle composite wing aircraft and is movably arranged on hybrid lift
The compound auxiliary wing composition of the airscrew thrust self energizing of aircraft two sides；Wherein, rear single-screw paddle composite wing aircraft includes machine
Body is fixedly mounted on body two sides hybrid lift wing, propeller；Wherein, body is set as deck platform；Hybrid lift wing
Built-in self-enclosed ducted fan, the outside design of hybrid lift wing have wing hinge；The compound auxiliary wing of airscrew thrust self energizing
Front end is provided with screw propeller, and the compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed ducted fan, spiral shell
The one or both sides of the rotation compound auxiliary wing of paddle thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and by wing hinge with
Hybrid lift wing is flexibly connected.Manned storehouse is mounted on the lower section of body.
Further, propeller is a variety of dynamic structures such as electric propeller, the dynamic propeller of oil.
Further, hybrid lift wing front and back are respectively set to magnetic-type self interlocking interface male connector and magnetic-type automatic
Mutual lock interface female；Magnetic-type self interlocking interface male connector is identical as magnetic-type self interlocking interface female size.
Further, magnetic-type self interlocking interface male connector and magnetic-type self interlocking interface female are taper connection
It further, further include vertical tail, the vertical tail is arranged above or below body；The vertical tail setting exists
Wing two sides；The vertical tail may be implemented to fold；Mobilizable vertical rudder wing is installed behind the vertical tail.
Further, body is installed with cavity, and installation diagram passes, flies the modules such as control, driving in cavity.
Further, the compound auxiliary wing of airscrew thrust self energizing can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance,
It is separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing；It is reserved between the auxiliary wing of lift and the auxiliary empennage of balance free
Between, the horizontal lifting rudder wing is provided in space；Wherein, a self-enclosed ducted fan is at least installed inside the auxiliary wing of lift.
Further, engine installation position is additionally provided on the compound auxiliary wing of airscrew thrust self energizing, in engine installation position
It is provided with power device.
Further, battery/fuel is provided on the compound auxiliary wing of airscrew thrust self energizing.
The prior art is compared, the main feature having is invented：
1. the present invention has landing apart from short, flying speed is fast, maneuverability, obstacle avoidance ability are strong, wing structure intensity is high, machine
The wing can be with energy storage, the features such as low energy consumption of flying.Self-enclosed vertical ducted fan is relied on, aircraft can be provided in horizontal flight
Additional maneuverability, realize moment change of flight posture and track super maneuver ability.
2. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention uses hybrid lift, i.e., existed by design
Self-enclosed ducted fan in aerofoil generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to be formed compound
Lift.
3. the Waverider wing that the present invention is very large, can play the role of certain paraglider, gravity acceleration is substantially reduced
Degree greatly improves safety coefficient, cooperates the control function of the hydroplane wing and the vertical rudder wing and the aerofoil envelope of self-enclosed ducted fan
Function is closed, even if lift ducted fan and horizontal propeller damage simultaneously, the forced landing of aerodone formula is also able to achieve, greatly improves
The safety of aircraft has ensured the safety of personnel and goods and materials.
4. the present invention uses hardware and software platform, modularized design, multiple functions are able to achieve,
5. the present invention using two 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, the cluster of aircraft is facilitated to fly, further decreases cluster flight
When power consumption.When front and back is connected in series, the aircraft at rear only needs a small amount of energy consumption, can be achieved with flying for long range
Row, the cluster flight of only aircraft does not provide the low-power consumption scheme of clustering, it might even be possible to realize the sky between aircraft
Faulty aircraft dragging below is taken off, realizes and mutually come to sb.'s rescue between aircraft not seen before by middle rescue, i.e., preceding aircraft
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 investment of client, reduces buying and operation cost.
8. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, synchronization is controlled by hybrid lift aircraft main control unit, is expanded 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 maintenance replacement.
10. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift flies
Energy intercommunication between device main plane, and the control by hybrid lift aircraft is acted, improve 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 are used, and have saved cost.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention；
Fig. 2 is side view of the invention；
Fig. 3 is rearview of the invention；
Fig. 4 is plan view of the invention；
Fig. 5 is oblique view of the 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：Fixation hole；1006：Battery/fuel；108：Video camera；
1026：Magnetic-type self interlocking interface male connector；1027：Spill series connection seat；1031, the compound auxiliary wing of airscrew thrust self energizing；
10311, the auxiliary wing of lift；10312, auxiliary empennage is balanced；1036, electro-hydraulic gas interface；10361, lid；111, engine installation position；
1062, screw propeller；112, manned storehouse.
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
As shown in Figures 1 to 5, with the rear single-screw paddle composite wing manned vehicle of the compound auxiliary wing of airscrew thrust, by
The compound auxiliary wing composition of single-screw paddle composite wing aircraft and the airscrew thrust self energizing for being assemblied in its wing two sides afterwards；
Wherein, the rear single-screw paddle composite wing aircraft includes body 101, to be fixedly mounted on 101 two sides of body compound
Lifting wing 102, propeller 106；Wherein, wherein the body 101 is set as deck platform；The hybrid lift machine
Self-enclosed ducted fan 104 built in the wing 102, design has wing hinge 1028 on the outside of hybrid lift wing 102；
The front end of the compound auxiliary wing of airscrew thrust self energizing is provided with screw propeller 1062, and airscrew thrust self energizing is compound
The auxiliary wing is internally provided with self-enclosed ducted fan 104, the one or both sides setting of the compound auxiliary wing of airscrew thrust self energizing
There are electro-hydraulic gas interface 1036 and wing hinge 1028, and be flexibly connected by wing hinge 1028 with hybrid lift wing 102,
In, the electro-hydraulic gas interface 1036 has lid 10361.
Manned storehouse 112 is mounted on the lower section of body.
As further improvement of the invention, propeller 106 is a variety of power knots such as electric propeller, the dynamic propeller of oil
Structure.
As further improvement of the invention, 102 front and back of hybrid lift wing are respectively set to magnetic-type self interlocking
Interface male connector 1026 and magnetic-type self interlocking interface female 1027；The magnetic-type self interlocking interface male connector 1026 and magnetic
Suction self interlocking interface 1027 sizes of female are identical.
As further improvement of the invention, magnetic-type self interlocking interface male connector 1026 and magnetic-type self interlocking interface
Female 1027 is taper connection,
It further include vertical tail 105, the vertical tail 105 is arranged above body 101 as further improvement of the invention
Or lower section；The vertical tail 105 is arranged in wing two sides；The vertical tail 105 may be implemented to fold；The vertical tail
Mobilizable vertical rudder wing 1051 is installed behind 105.
Improved as of the invention further, body 101 is installed with cavity 1002, in cavity 1002 installation diagram pass, fly control,
The modules such as driving.
Improved as of the invention further, the compound auxiliary wing of airscrew thrust self energizing can be divided into the auxiliary wing 10311 of lift with
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 airscrew thrust self energizing；The auxiliary wing of lift
It is reserved with space between 10311 and the auxiliary empennage 10312 of balance, the horizontal lifting rudder wing 1022 is provided in space；Wherein, lift is auxiliary
One self-enclosed ducted fan 104 is at least installed inside the wing 10311.
As further improvement of the invention, engine installation position is additionally provided on the compound auxiliary wing of airscrew thrust self energizing
111, power device is provided in engine installation position 111.
As further improvement of the invention, battery/fuel 1006 is provided on the compound auxiliary wing of airscrew thrust self energizing.
The prior art is compared, the main feature having is invented：
1. the present invention has landing apart from short, flying speed is fast, maneuverability, obstacle avoidance ability are strong, wing structure intensity is high, machine
The wing can be with energy storage, the features such as low energy consumption of flying.Self-enclosed vertical ducted fan is relied on, aircraft can be provided in horizontal flight
Additional maneuverability, realize moment change of flight posture and track super maneuver ability.
2. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention uses hybrid lift, i.e., existed by design
Self-enclosed ducted fan in aerofoil generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to be formed compound
Lift.
3. the Waverider wing that the present invention is very large, can play the role of certain paraglider, gravity acceleration is substantially reduced
Degree greatly improves safety coefficient, cooperates the control function of the hydroplane wing and the vertical rudder wing and the aerofoil envelope of self-enclosed ducted fan
Function is closed, even if lift ducted fan and horizontal propeller damage simultaneously, the forced landing of aerodone formula is also able to achieve, greatly improves
The safety of aircraft has ensured the safety of personnel and goods and materials.
4. the present invention uses hardware and software platform, modularized design, multiple functions are able to achieve,
5. the present invention using two 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, the cluster of aircraft is facilitated to fly, further decreases cluster flight
When power consumption.When front and back is connected in series, the aircraft at rear only needs a small amount of energy consumption, can be achieved with flying for long range
Row, the cluster flight of only aircraft does not provide the low-power consumption scheme of clustering, it might even be possible to realize the sky between aircraft
Faulty aircraft dragging below is taken off, realizes and mutually come to sb.'s rescue between aircraft not seen before by middle rescue, i.e., preceding aircraft
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 investment of client, reduces buying and operation cost.
8. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, synchronization is controlled by hybrid lift aircraft main control unit, is expanded 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 maintenance replacement.
10. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift flies
Energy intercommunication between device main plane, and the control by hybrid lift aircraft is acted, improve 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 are used, and have saved cost.
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, should belong to the scope of the present invention.
Claims (9)
1. the rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust, which is characterized in that by rear single spiral shell
The compound rotor aircraft of rotary propeller type and the compound auxiliary wing composition of the airscrew thrust self energizing for being assemblied in its wing two sides；
Wherein, the rear single-screw paddle composite wing aircraft includes body（101）, be fixedly mounted on body（101）Two sides
Hybrid lift wing（102）, propeller（106）；Wherein, the body（101）It is set as deck platform；The compound liter
Power wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside design has wing hinge (1028)；
Propeller（106）For screw propeller；
The front end of the compound auxiliary wing of the airscrew thrust self energizing is provided with screw propeller（1062）, airscrew thrust is certainly
Energize the compound auxiliary wing is internally provided with self-enclosed ducted fan（104）, the side of the compound auxiliary wing of airscrew thrust self energizing or
Two sides are provided with electro-hydraulic gas interface（1036）With wing hinge (1028), and pass through wing hinge (1028) and hybrid lift wing
（102）It is flexibly connected, wherein the electro-hydraulic gas interface（1036）With lid（10361）；
The manned storehouse（112 are mounted on the lower section of body.
2. the rear single-screw paddle composite wing manned vehicle according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the propeller（106）For a variety of dynamic structures such as electric propeller, the dynamic propellers of oil.
3. the rear single-screw paddle composite wing manned vehicle according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the hybrid lift wing（102）Front and back are respectively set to magnetic-type self interlocking interface male connector
（1026）With magnetic-type self interlocking interface female（1027）；The magnetic-type self interlocking interface male connector（1026）With magnetic
Formula self interlocking interface female（1027）Size is identical.
4. the rear single-screw paddle composite wing manned vehicle according to claim 3 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the magnetic-type self interlocking interface male connector（1026）With magnetic-type self interlocking interface female（1027）For cone
Shape connection.
5. the rear single-screw paddle composite wing manned vehicle according to claim 1 with the compound auxiliary wing of airscrew thrust,
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 two sides；The vertical tail（105）It may be implemented to fold；The vertical tail（105）
Mobilizable vertical rudder wing is installed below（1051）.
6. the rear single-screw paddle composite wing manned vehicle according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the body（101）It is installed with cavity（1002）, cavity（1002）Interior installation diagram passes, flies the moulds such as control, driving
Block.
7. the rear single-screw paddle composite wing manned vehicle according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the compound auxiliary wing of the airscrew 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 airscrew 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）Inside is at least equipped with a self-enclosed ducted fan（104）.
8. the rear single-screw paddle composite wing manned vehicle according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, being additionally provided with engine installation position on the compound auxiliary wing of the airscrew thrust self energizing（111）, engine peace
Fill position（111）Inside it is provided with power device.
9. the rear single-screw paddle composite wing manned vehicle according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, being provided with battery/fuel on the compound auxiliary wing of the airscrew thrust self energizing（1006）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810551068.7A CN108820201A (en) | 2018-05-31 | 2018-05-31 | Rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810551068.7A CN108820201A (en) | 2018-05-31 | 2018-05-31 | Rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108820201A true CN108820201A (en) | 2018-11-16 |
Family
ID=64146572
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810551068.7A Pending CN108820201A (en) | 2018-05-31 | 2018-05-31 | Rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108820201A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110282114A (en) * | 2019-07-17 | 2019-09-27 | 王颖 | It is a kind of for Reservoir region cruise can VTOL composite wing electric power unmanned plane |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030062443A1 (en) * | 2001-10-02 | 2003-04-03 | Joseph Wagner | VTOL personal aircraft |
| 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 |
| CN206107569U (en) * | 2016-09-26 | 2017-04-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle |
| CN107813929A (en) * | 2016-09-11 | 2018-03-20 | 郎风 | Combined type dalta wing duct aircraft |
-
2018
- 2018-05-31 CN CN201810551068.7A patent/CN108820201A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030062443A1 (en) * | 2001-10-02 | 2003-04-03 | Joseph Wagner | VTOL personal aircraft |
| 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 |
| CN206107569U (en) * | 2016-09-26 | 2017-04-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110282114A (en) * | 2019-07-17 | 2019-09-27 | 王颖 | It is a kind of for Reservoir region cruise can VTOL composite wing electric power unmanned plane |
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Application publication date: 20181116 |