CN108839797A - A kind of spiral shell with additional fin pushes away the manned aircraft of composite wing - Google Patents
A kind of spiral shell with additional fin pushes away the manned aircraft of composite wing Download PDFInfo
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- CN108839797A CN108839797A CN201810551409.0A CN201810551409A CN108839797A CN 108839797 A CN108839797 A CN 108839797A CN 201810551409 A CN201810551409 A CN 201810551409A CN 108839797 A CN108839797 A CN 108839797A
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- China
- Prior art keywords
- wing
- additional fin
- aircraft
- pushes away
- spiral shell
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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
- B64C27/20—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)
- Toys (AREA)
Abstract
The present invention is that a kind of spiral shell with additional fin pushes away the manned aircraft of composite wing, wherein rear single-screw paddle composite wing aircraft includes body, the additional fin for being assemblied in its wing two sides and manned storehouse；Self-enclosed ducted fan built in hybrid lift wing, the outside design of hybrid lift wing have wing hinge；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；Electro-hydraulic gas interface has lid, additional fin internal battery/fuel；Manned storehouse is mounted on the lower section of body.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, highly-safe the features such as, 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 movement is improved the flexibility of complete machine by the control of hybrid lift aircraft.
Description
Technical field
The present invention relates to a kind of aircraft, specifically a kind of spiral shell with additional fin pushes away the manned aircraft of composite wing, belongs to flight
Device 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, 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 two sides
Additional fin and manned storehouse；Wherein, rear single-screw paddle composite wing aircraft includes body, to be fixedly mounted on body two sides multiple
Close lifting wing, screw propeller；Wherein, body is set as deck platform；Self-enclosed duct wind built in hybrid lift wing
Fan, the outside design of hybrid lift wing have wing hinge；The side of additional fin towards body is provided with wing hinge and electro-hydraulic gas
Interface, and be mounted on the outside of hybrid lift wing by the way that wing hinge is folding；Electro-hydraulic gas interface has lid, in additional fin
Set battery/fuel.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
Further, hybrid lift wing can be divided into lift main wing and balance two parts of 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,
One self-enclosed ducted fan is at least installed inside lift main wing.
It further, further include vertical tail, the vertical tail is arranged above or below body；The vertical tail is set
It sets in 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, 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 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.
3. the present invention uses hardware and software platform, modularized design, multiple functions are able to achieve,
4. 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.
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.When front and back is connected in series, the aircraft at rear only needs a small amount of energy consumption, energy
Realize the flight of long range, the cluster flight of only aircraft does not provide 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 maintenance replacement.
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 the control by hybrid lift aircraft is acted, improve the flexibility of complete machine.
8. aerofoil type energy device efficiently uses space.
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；
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；112, manned storehouse；114, additional fin.
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
As shown in Figures 1 to 5, a kind of spiral shell with additional fin pushes away the manned aircraft of composite wing, including rear single-screw paddle is compound
Rotor aircraft, the additional fin 114 for being assemblied in its wing two sides and manned storehouse 112；Wherein, the rear single-screw paddle is compound
Rotor aircraft includes body 101, is fixedly mounted on 101 two sides hybrid lift wing 102 of body, propeller 106；Wherein, described
Body 101 be set as deck platform；Self-enclosed ducted fan 104, hybrid lift machine built in the hybrid lift wing 102
Design has wing hinge (1028) on the outside of the wing 102；The side of additional fin 114 towards the body 101 is provided with wing hinge
1028 and electro-hydraulic gas interface 1036, and 102 outside of hybrid lift wing is mounted on by the way that wing hinge 1028 is folding；It is described
Electro-hydraulic gas interface 1036 have lid 10361,114 internal batteries of additional fin/fuel 1006.Manned storehouse 112 is mounted on body
101 lower section.
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, be at least equipped with inside lift main wing 1,021 one it is self-enclosed
Ducted fan 104.
It further include vertical tail 105, the vertical tail 105 is arranged in body 101 as further improvement of the invention
Above or below；The vertical tail 105 is arranged in wing two 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, 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 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.
3. the present invention uses hardware and software platform, modularized design, multiple functions are able to achieve,
4. 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.
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.When front and back is connected in series, the aircraft at rear only needs a small amount of energy consumption, energy
Realize the flight of long range, the cluster flight of only aircraft does not provide 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 maintenance replacement.
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 belong to the scope of the present invention.
Claims (7)
1. a kind of spiral shell with additional fin pushes away the manned aircraft of composite wing, which is characterized in that fly including rear single-screw paddle composite wing
Device, the additional fin for being assemblied in its wing two sides（114）And manned storehouse（112）；
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 additional fin（114）Towards body（101）Side be provided with wing hinge (1028) and electro-hydraulic gas interface
（1036）, and hybrid lift wing is mounted on by the way that wing hinge (1028) are folding（102）Outside；The electro-hydraulic gas connects
Mouthful（1036）With lid（10361）, additional fin（114）Internal battery/fuel（1006）；
The manned storehouse（112）It is mounted on body（101）Lower section.
2. a kind of spiral shell with additional fin according to claim 1 pushes away the manned aircraft of composite wing, which is characterized in that described pushes away
Into device（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 the manned aircraft of composite wing, which is characterized in that described answers
Close lifting wing（102）Front and back are respectively set to magnetic-type self interlocking interface male connector（1036）With magnetic-type automatic mutual interlocking
Mouth female（1027）；The magnetic-type self interlocking interface male connector（1036）With magnetic-type self interlocking interface female（1027）
Size is identical.
4. a kind of spiral shell with additional fin according to claim 3 pushes away the manned aircraft of composite wing, which is characterized in that the magnetic
Formula self interlocking interface male connector（1036）With magnetic-type self interlocking interface female（1027）For taper connection.
5. a kind of spiral shell with additional fin according to claim 1 pushes away the manned aircraft of composite wing, which is characterized in that described answers
Close lifting wing（102）Lift main wing can be divided into（1021）And balance empennage（1023）Two parts, are separately positioned on compound
Lifting wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between be reserved with space, be arranged in space
There is the horizontal lifting rudder wing（1022）；Wherein, lift main wing（1021）Inside is at least equipped with a self-enclosed ducted fan
（104）.
6. a kind of spiral shell with additional fin according to claim 1 pushes away the manned aircraft of composite wing, which is characterized in that further include hanging down
Straight tail（105）, the vertical tail（105）It is arranged in body（101）Above or below；The vertical tail（105）Setting
In wing two sides；The vertical tail（105）It may be implemented to fold；The vertical tail（105）It is equipped with below mobilizable
The vertical rudder wing（1051）.
7. a kind of spiral shell with additional fin according to claim 1 pushes away the manned aircraft of composite wing, which is characterized in that the machine
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 |
|---|---|---|---|
| CN201810551409.0A CN108839797A (en) | 2018-05-31 | 2018-05-31 | A kind of spiral shell with additional fin pushes away the manned aircraft of composite wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810551409.0A CN108839797A (en) | 2018-05-31 | 2018-05-31 | A kind of spiral shell with additional fin pushes away the manned aircraft of composite wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108839797A true CN108839797A (en) | 2018-11-20 |
Family
ID=64211146
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810551409.0A Pending CN108839797A (en) | 2018-05-31 | 2018-05-31 | A kind of spiral shell with additional fin pushes away the manned aircraft of composite wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108839797A (en) |
Citations (9)
| 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 |
| US20040245374A1 (en) * | 2003-01-06 | 2004-12-09 | Morgan Brian H. | Vertical take-off and landing aircraft |
| US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
| CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
| CN102616096A (en) * | 2012-04-24 | 2012-08-01 | 赵辉 | Solar flying automobile with folding wings |
| CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
| WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
-
2018
- 2018-05-31 CN CN201810551409.0A patent/CN108839797A/en active Pending
Patent Citations (9)
| 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 |
| US20040245374A1 (en) * | 2003-01-06 | 2004-12-09 | Morgan Brian H. | Vertical take-off and landing aircraft |
| US20100051741A1 (en) * | 2008-09-03 | 2010-03-04 | Anvar Ismailov | Unmanned air vehicle |
| CN102530248A (en) * | 2011-12-12 | 2012-07-04 | 周景荣 | Design method for multifunctional helicopter |
| CN102616096A (en) * | 2012-04-24 | 2012-08-01 | 赵辉 | Solar flying automobile with folding wings |
| CN102658866A (en) * | 2012-05-25 | 2012-09-12 | 辽宁通用航空研究院 | Conjoined aircraft with straight layout |
| CN107089316A (en) * | 2016-02-18 | 2017-08-25 | 张飞 | Flying wing type dual-culvert vertical take-off and landing aircraft |
| WO2018078388A1 (en) * | 2016-10-27 | 2018-05-03 | Mono Aerospace Ip Ltd | Vertical take-off and landing aircraft and control method |
| CN107651168A (en) * | 2017-09-30 | 2018-02-02 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane wingfold mechanism and method for folding |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181120 |
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