CN108750094A - A kind of spiral shell with additional fin pushes away combined wing aircraft - Google Patents
A kind of spiral shell with additional fin pushes away combined wing aircraft Download PDFInfo
- Publication number
- CN108750094A CN108750094A CN201810550362.6A CN201810550362A CN108750094A CN 108750094 A CN108750094 A CN 108750094A CN 201810550362 A CN201810550362 A CN 201810550362A CN 108750094 A CN108750094 A CN 108750094A
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- Prior art keywords
- wing
- additional fin
- aircraft
- propeller
- hybrid lift
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- 239000002131 composite material Substances 0.000 claims abstract description 8
- 238000009434 installation Methods 0.000 claims description 7
- 150000001875 compounds Chemical class 0.000 claims description 4
- 238000010586 diagram Methods 0.000 claims description 4
- 239000000446 fuel Substances 0.000 claims description 4
- 238000005265 energy consumption Methods 0.000 abstract description 7
- 238000004146 energy storage Methods 0.000 abstract description 4
- 230000009471 action Effects 0.000 abstract description 2
- 230000006872 improvement Effects 0.000 description 5
- 239000000463 material Substances 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003643 water by type Substances 0.000 description 1
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The present invention is that a kind of spiral shell with additional fin pushes away combined wing aircraft, including rear single-screw paddle composite wing aircraft, the additional fin for being assemblied in its wing both sides；Single-screw paddle composite wing aircraft includes body, is fixedly mounted on body both sides hybrid lift wing, propeller afterwards；Body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, hybrid lift wing outside are designed with wing hinge；Propeller is screw propeller；The side of additional fin towards body is provided with wing hinge and electro-hydraulic gas interface, and is mounted on the outside of hybrid lift wing by the way that wing hinge is folding.The present invention not only has landing apart from short, wing can be with energy storage, the features such as low energy consumption, the hang time is long, safe of flying, additional fin one or both sides are provided with electro-hydraulic gas interface, realize the additional energy intercommunication between hybrid lift aircraft main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
Description
Technical field
The present invention relates to a kind of aircraft, specifically a kind of spiral shell with additional fin pushes away combined wing aircraft, belongs to aircraft dress
Standby technical 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, hydrous waters
The flat rudder wing can play the role of aerodone under case of emergency, 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 assemblied in its wing both sides
Additional fin；Wherein, rear single-screw paddle composite wing aircraft includes body, is fixedly mounted on body both sides hybrid lift machine
The wing, screw propeller；Wherein, body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, compound liter
It is designed with wing hinge on the outside of power wing；The side of additional fin towards body is provided with wing hinge and electro-hydraulic gas interface, and leads to
It is folding on the outside of hybrid lift wing to cross wing hinge；Electro-hydraulic gas interface carries lid, additional fin internal battery/combustion
Material.
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
Further, hybrid lift wing can be divided into two parts of lift main wing and balance empennage, be separately positioned on hybrid lift
The front and back of wing；It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space；Wherein,
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 installed with cavity, and installation diagram passes, flies the modules such as control, driving in cavity.
Further, it is provided with battery/fuel 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, 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 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, coordinates 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 can realize that aerodone formula is force-landed if damage simultaneously, is greatly improved
The safety of aircraft 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 magnetic-type self interlocking interface, the cluster of aircraft is facilitated to fly, into one
Step reduces power consumption when cluster flight.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, energy
Realize the flight of long range, the not cluster flight of only aircraft provides the low-power consumption scheme of clustering, it might even be possible to realize
Air rescue between aircraft, i.e., preceding aircraft take off faulty aircraft dragging below, realize not seen before fly
Phenomenon is rescued mutually between row device.
6. thrust device modularization can very easily realize that repair is replaced.
7. in the present invention, additional fin one or both sides are provided with electro-hydraulic gas interface, realize additional and hybrid lift and fly
Energy intercommunication between device main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
8. aerofoil type energy device, efficiently uses space.
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；
1036：Magnetic-type self interlocking interface male connector；1027：Magnetic-type self interlocking interface female；1036, electro-hydraulic gas interface；
10361, lid；111, engine installation position；114, additional fin.
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 spiral shell with additional fin pushes away combined wing aircraft, including rear single-screw paddle composite wing flies
Row device, the additional fin 114 for being assemblied in its wing both sides；Wherein, the rear single-screw paddle composite wing aircraft includes body
101,101 both sides hybrid lift wing 102 of body, propeller 106 are fixedly mounted on；Wherein, the body 101 is set as first
Plate platform；Self-enclosed ducted fan 104 built in the hybrid lift wing 102, the 102 outside design of hybrid lift wing are organic
Wing hinge 1028；The side of additional fin 114 towards the body 101 is provided with wing hinge 1028 and electro-hydraulic gas interface
1036, and it is mounted on 102 outside of hybrid lift wing by the way that wing hinge 1028 is folding；The electro-hydraulic gas interface 1036
With lid 10361,114 internal batteries of additional fin/fuel 1006.
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 1036 and magnetic-type self interlocking interface female 1027；The magnetic-type self interlocking interface male connector 1036 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 1036 and magnetic-type self interlocking interface
Female 1027 is taper connection,
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；It is reserved between lift main wing 1021 and balance empennage 1023
There is space, the horizontal lifting rudder wing 1022 is provided in space；Wherein, at least there are one self-enclosed for installation inside lift main wing 1021
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.
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.
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, 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 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, coordinates 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 can realize that aerodone formula is force-landed if damage simultaneously, is greatly improved
The safety of aircraft 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 magnetic-type self interlocking interface, the cluster of aircraft is facilitated to fly, into one
Step reduces power consumption when cluster flight.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, energy
Realize the flight of long range, the not cluster flight of only aircraft provides the low-power consumption scheme of clustering, it might even be possible to realize
Air rescue between aircraft, i.e., preceding aircraft take off faulty aircraft dragging below, realize not seen before fly
Phenomenon is rescued mutually between row device.
6. thrust device modularization can very easily realize that repair is replaced.
7. in the present invention, aerofoil type energy device efficiently uses space.
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 all belong to the scope of the present invention.
Claims (6)
1. a kind of spiral shell with additional fin pushes away combined wing aircraft, which is characterized in that including rear single-screw paddle composite wing aircraft, dress
Fit over the additional fin of its wing both sides（114）；
Wherein, the rear single-screw paddle composite wing aircraft includes body（101）, be fixedly mounted on body（101）Both 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 is designed with wing hinge (1028)；
Propeller（106）For screw propeller；
The additional fin（114）Towards body（101）Side be provided with wing hinge (1028) and electro-hydraulic gas interface
（1036）, and it is mounted on hybrid lift wing by the way that wing hinge (1028) is folding（102）Outside；The electro-hydraulic gas connects
Mouthful（1036）With lid（10361）, additional fin（114）Internal battery/fuel（1006）.
2. a kind of spiral shell with additional fin according to claim 1 pushes away combined wing aircraft, which is characterized in that the propeller
（106）For a variety of dynamic structures such as electric propeller, the dynamic propellers of oil.
3. a kind of spiral shell with additional fin according to claim 1 pushes away combined wing aircraft, which is characterized in that the compound liter
Power wing（102）Front and back are respectively set to magnetic-type self interlocking interface male connector（1036）With magnetic-type self interlocking interface mother
Head（1027）；The magnetic-type self interlocking interface male connector（1036）With magnetic-type self interlocking interface female（1027）Size
It is identical.
4. a kind of spiral shell with additional fin according to claim 3 pushes away combined wing aircraft, which is characterized in that described is magnetic-type
Self interlocking interface male connector（1036）With magnetic-type self interlocking interface female（1027）For taper connection,
The hybrid lift wing（102）Lift main wing can be divided into（1021）And balance empennage（1023）Two parts, point
It is not arranged in hybrid lift wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between reserve it is free
Between, the horizontal lifting rudder wing is provided in space（1022）；Wherein, lift main wing（1021）There are one self-enclosed for internal at least installation
Ducted fan（104）.
5. a kind of spiral shell with additional fin according to claim 1 pushes away combined wing aircraft, which is characterized in that further include vertical end
The wing（105）, the vertical tail（105）It is arranged in body（101）Above or below；The vertical tail（105）It is arranged in machine
Wing both sides；The vertical tail（105）It may be implemented to fold；The vertical tail（105）It is equipped with below mobilizable vertical
The rudder wing（1051）.
6. a kind of spiral shell with additional fin according to claim 1 pushes away combined wing aircraft, which is characterized in that the body
（101）It is installed with cavity（1002）, cavity（1002）Interior installation diagram passes, flies the modules such as control, driving.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810550362.6A CN108750094A (en) | 2018-05-31 | 2018-05-31 | A kind of spiral shell with additional fin pushes away combined wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810550362.6A CN108750094A (en) | 2018-05-31 | 2018-05-31 | A kind of spiral shell with additional fin pushes away combined wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108750094A true CN108750094A (en) | 2018-11-06 |
Family
ID=64001469
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810550362.6A Pending CN108750094A (en) | 2018-05-31 | 2018-05-31 | A kind of spiral shell with additional fin pushes away combined wing aircraft |
Country Status (1)
| Country | Link |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3972490A (en) * | 1975-03-07 | 1976-08-03 | Mcdonnell Douglas Corporation | Trifan powered VSTOL aircraft |
| DE2736120A1 (en) * | 1976-08-14 | 1978-02-16 | Rolls Royce | AXIAL FAN, ESPECIALLY AS A PULLER FOR AIRCRAFT, WITH INCLUDING AND RELEASABLE COUPLING |
| US4469294A (en) * | 1982-05-20 | 1984-09-04 | Clifton Robert T | V/STOL Aircraft |
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| 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 CN201810550362.6A patent/CN108750094A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3972490A (en) * | 1975-03-07 | 1976-08-03 | Mcdonnell Douglas Corporation | Trifan powered VSTOL aircraft |
| DE2736120A1 (en) * | 1976-08-14 | 1978-02-16 | Rolls Royce | AXIAL FAN, ESPECIALLY AS A PULLER FOR AIRCRAFT, WITH INCLUDING AND RELEASABLE COUPLING |
| US4469294A (en) * | 1982-05-20 | 1984-09-04 | Clifton Robert T | V/STOL Aircraft |
| US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
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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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181106 |