CN108674646A - With without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing - Google Patents
With without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing Download PDFInfo
- Publication number
- CN108674646A CN108674646A CN201810549827.6A CN201810549827A CN108674646A CN 108674646 A CN108674646 A CN 108674646A CN 201810549827 A CN201810549827 A CN 201810549827A CN 108674646 A CN108674646 A CN 108674646A
- Authority
- CN
- China
- Prior art keywords
- wing
- ducted fan
- compound
- compound auxiliary
- aircraft
- 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
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The present invention is a kind of hybrid lift aircraft of band expansion platform, by the compound rotor aircraft of rear list ducted fan formula, is assemblied in being formed without the compound auxiliary wing of thrust self energizing, shipping storehouse for its both sides；Wherein, rear single compound rotor aircraft of ducted fan formula includes body, is fixedly 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；It is provided with self-enclosed ducted fan 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 be flexibly connected with hybrid lift wing by wing hinge, shipping storehouse is mounted on the lower section of body.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 hybrid lift wing of large area, 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 band is without the rear single ducted fan formula composite wing for pushing away the compound auxiliary wing
Cargo 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 and goods and materials.
To achieve the goals above, the present invention by the compound rotor aircraft of rear single ducted fan formula, be movably arranged on compound liter
Power aircraft both sides are formed without the compound auxiliary wing of thrust self energizing, shipping storehouse；Wherein, rear single ducted fan formula composite wing
Aircraft includes body, is fixedly mounted on body both sides hybrid lift wing, propeller；Wherein, the body is set as first
Plate platform；Self-enclosed ducted fan built in the hybrid lift wing, hybrid lift wing outside are designed with wing hinge；It pushes away
It is ducted fan propeller into device；It is provided with self-enclosed ducted fan, no thrust self energizing in the no compound auxiliary wing of thrust self energizing
The one or both sides of the compound auxiliary wing are provided with electro-hydraulic gas interface and wing hinge, and are lived by wing hinge and hybrid lift wing
Dynamic connection；The no compound auxiliary wing of thrust self energizing can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance, be separately positioned on nothing
Wherein, at least there are one self-enclosed ducted fan, shippings for installation inside the auxiliary wing of lift by the front and back of the compound auxiliary wing of thrust self energizing
Storehouse is mounted on the lower section of body.
Further, hybrid lift wing can be divided into two parts of lift main wing and balance empennage, be separately positioned on compound
Lifting wing front and back；Lift main wing）It is reserved with space between 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；The vertical tail（105）It is equipped with below mobilizable vertical
The rudder wing.
Further, the vertical rudder wing is movably connected in the rear of vertical tail,.
Further, vertical tail, forms an angle with body planar shaped, and haulage gear is equipped on vertical tail, realizes vertical
The deflection of the rudder wing.
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, it is provided with video camera in front of body, video camera is monopod video camera.
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, 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.
3, the present invention can realize multiple functions using hardware and software platform, modularized design,
4, 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. 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.
7. 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.
8. thrust device modularization can very easily realize that repair is replaced.
9. in the 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.
10. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
11. aerofoil type energy device, efficiently uses space.
12. 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；
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；10311, lift is auxiliary
The wing；10312, auxiliary empennage is balanced；1036, electro-hydraulic gas interface；10361, lid；108, video camera；113, shipping storehouse.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
As shown in Figure 1, a kind of band, without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing, feature exists
In, by the compound rotor aircraft of rear single ducted fan formula, be assemblied in its wing both sides without the compound auxiliary wing of thrust self energizing, shipping storehouse
Composition；
Wherein, described rear single compound rotor aircraft of ducted fan formula includes body 101, to be fixedly mounted on 101 both sides of body multiple
Close lifting wing 102, propeller 106；Wherein, the body 101 is set as deck platform；The hybrid lift wing
Self-enclosed ducted fan 104 built in 102,102 outside of hybrid lift wing are designed with wing hinge 1028；The propeller
106 be ducted fan propeller；
It is described without being provided with self-enclosed ducted fan 104, no compound auxiliary wing of thrust self energizing in the compound auxiliary wing of thrust self energizing
One or both sides be provided with electro-hydraulic gas interface 1036 and wing hinge (1028), and pass through wing hinge (1028) and compound liter
Power wing 102 is flexibly connected；The no compound auxiliary wing of thrust self energizing can be divided into the auxiliary wing 10311 of lift and balance auxiliary empennage 10312
Two parts are separately positioned on the front and back of the compound auxiliary wing of no thrust self energizing wherein, at least pacify inside the auxiliary wing of lift 10311
There are one self-enclosed ducted fans 104 for dress.
Shipping storehouse 113 is mounted on the lower section of body 101.
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.
Further include vertical tail 105 as further improvement of the invention, the vertical tail 105 is arranged in body 101
Above or below；The vertical tail 105 is arranged in wing both sides；The vertical tail 105 may be implemented to fold；It is described vertical
Mobilizable vertical rudder wing 1051 is installed behind empennage 105.
As further improvement of the invention, the vertical rudder wing 1051 is movably connected in the rear of vertical tail, 105.
As further improvement of the invention, vertical tail, 105 forms an angle with body planar shaped, and is installed on vertical tail,
There is haulage gear, realizes the deflection of the vertical rudder wing.
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 1036 carries lid 10361.
As further improvement of the invention, 101 front of body is provided with video camera 108, and video camera 108 is that holder images
Machine.
As further improvement of the invention, battery/fuel 1006 is provided on the no compound auxiliary wing of 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, 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.
3, the present invention can realize multiple functions using hardware and software platform, modularized design,
4, 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.
5, 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.
6. 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.
7. 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.
8. thrust device modularization can very easily realize that repair is replaced.
9. in the 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.
10. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
11. aerofoil type energy device, efficiently uses space.
12. 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 (9)
1. a kind of band is without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing, which is characterized in that by rear Dan Han
The compound rotor aircraft of road fan-type, be assemblied in its wing both sides without the compound auxiliary wing of thrust self energizing, shipping storehouse（113）Composition；
Wherein, rear single compound rotor aircraft of ducted fan formula includes body（101）, be fixedly mounted on body（101）Two
Side hybrid lift wing（102）, propeller（106）；Wherein, the body（101）It is set as deck platform；Described is compound
Lifting wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside is designed with wing hinge
(1028)；The propeller（106）For ducted fan 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（1036）With wing hinge (1028), and by wing hinge (1028) with it is multiple
Close lifting wing（102）Flexible connection；The no compound auxiliary wing of thrust self energizing can be divided into the auxiliary wing of lift（10311）And the auxiliary tail of balance
The wing（10312）Two parts are separately positioned on the front and back of the compound auxiliary wing of no thrust self energizing wherein, the auxiliary wing of lift（10311）
There are one self-enclosed ducted fans for internal at least installation（104）；
The shipping storehouse（113）Mounted on body（101）Lower section.
2. a kind of band according to claim 1 is without the rear single ducted fan formula composite wing cargo aircraft 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）.
3. a kind of band according to claim 1 is without the rear single ducted fan formula composite wing cargo aircraft 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）.
4. a kind of band according to claim 3 is without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing,
It is characterized in that, the vertical rudder wing（1051）It is movably connected in vertical tail,（105）Rear.
5. a kind of band according to claim 3 is without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing,
It is characterized in that, the vertical tail,（105）It forms an angle with body planar shaped, and haulage gear is installed on vertical tail,
Realize the deflection of the vertical rudder wing.
6. a kind of band according to claim 1 is without the rear single ducted fan formula composite wing cargo aircraft 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 single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing,
It is characterized in that, the electro-hydraulic gas interface（1036）With lid（10361）.
8. a kind of band according to claim 1 is without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing,
It is characterized in that, the body（101）Front is provided with video camera（108）, video camera（108）For monopod video camera.
9. a kind of band according to claim 1 is without the rear single ducted fan formula composite wing cargo aircraft 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 |
|---|---|---|---|
| CN201810549827.6A CN108674646A (en) | 2018-05-31 | 2018-05-31 | With without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810549827.6A CN108674646A (en) | 2018-05-31 | 2018-05-31 | With without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108674646A true CN108674646A (en) | 2018-10-19 |
Family
ID=63809463
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810549827.6A Pending CN108674646A (en) | 2018-05-31 | 2018-05-31 | With without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108674646A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| US8146855B2 (en) * | 2008-09-03 | 2012-04-03 | Anvar Ismailov | Unmanned air vehicle |
| CN202414160U (en) * | 2011-11-15 | 2012-09-05 | 成都飞机设计研究所 | Vertical take-off and landing morphing aircraft |
| CN103419942A (en) * | 2013-09-10 | 2013-12-04 | 北京臻迪科技有限公司 | Unmanned aerial vehicle |
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
-
2018
- 2018-05-31 CN CN201810549827.6A patent/CN108674646A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| US8146855B2 (en) * | 2008-09-03 | 2012-04-03 | Anvar Ismailov | Unmanned air vehicle |
| CN202414160U (en) * | 2011-11-15 | 2012-09-05 | 成都飞机设计研究所 | Vertical take-off and landing morphing aircraft |
| CN103419942A (en) * | 2013-09-10 | 2013-12-04 | 北京臻迪科技有限公司 | Unmanned aerial vehicle |
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108545183A (en) | Rear single ducted fan formula composite wing cargo aircraft with solar energy additional fin | |
| CN108466691A (en) | The compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan | |
| CN108725772A (en) | A kind of band is without the rear single-screw paddle composite wing aircraft for pushing away the compound auxiliary wing | |
| CN108657424A (en) | Rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust | |
| CN108674647A (en) | The rear manned aircraft of single-blade formula composite wing of the band double compound auxiliary wings of duct thrust and the auxiliary wing | |
| CN108820201A (en) | Rear single-screw paddle composite wing manned vehicle with the compound auxiliary wing of airscrew thrust | |
| CN108791861A (en) | With without the rear single ducted fan formula composite wing manned vehicle for pushing away the compound auxiliary wing | |
| CN108773486A (en) | It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula | |
| CN108528706A (en) | The composite wing airfreighter of the compound auxiliary wing of twin screw with solar energy additional fin | |
| CN108791871A (en) | Rear single ducted fan formula composite wing airfreighter with the compound auxiliary wing and additional fin | |
| CN108750088A (en) | Rear single screw folding composite wing cargo aircraft with the compound auxiliary wing of thrust | |
| CN108466693A (en) | Rear single ducted fan formula composite wing airfreighter with the compound auxiliary wing and additional fin | |
| CN108791813A (en) | Rear single vortex-spraying type composite wing cargo aircraft with solar energy additional fin | |
| CN108466692A (en) | The manned aircraft of rear single ducted fan formula composite wing with the compound auxiliary wing and additional fin | |
| CN108482663A (en) | The rear single-blade formula combined wing aircraft of the double duct thrusts of the band compound auxiliary wing and additional fin | |
| CN108820202A (en) | It is a kind of with the compound auxiliary wing of ducted fan without the compound rotor aircraft of back pressure formula | |
| CN108674646A (en) | With without the rear single ducted fan formula composite wing cargo aircraft for pushing away the compound auxiliary wing | |
| CN108502163A (en) | With without the compound rotor aircraft of rear single ducted fan formula for pushing away the compound auxiliary wing | |
| CN108528702A (en) | A kind of band is without the rear single-screw paddle composite wing manned vehicle for pushing away the compound auxiliary wing | |
| CN108528700A (en) | With without the rear single screw folding composite wing manned vehicle for pushing away the compound auxiliary wing | |
| CN108750096A (en) | A kind of band is without the rear single-screw paddle composite wing cargo aircraft for pushing away the compound auxiliary wing | |
| CN108791870A (en) | Double culverts push away the compound auxiliary wing and rear single culvert pushing-type composite wing cargo aircraft of additional fin | |
| CN108791862A (en) | Double culverts push away the compound auxiliary wing and rear single culvert pushing-type composite wing manned vehicle of additional fin | |
| CN108773487A (en) | Rear single-screw paddle composite wing cargo aircraft with the compound auxiliary wing and additional fin | |
| CN108502165A (en) | A kind of rear single-screw paddle composite wing aircraft of the band compound auxiliary wing and additional fin |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181019 |