CN108839796A - A kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust - Google Patents
A kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust Download PDFInfo
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- CN108839796A CN108839796A CN201810551182.XA CN201810551182A CN108839796A CN 108839796 A CN108839796 A CN 108839796A CN 201810551182 A CN201810551182 A CN 201810551182A CN 108839796 A CN108839796 A CN 108839796A
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- Prior art keywords
- wing
- self
- compound auxiliary
- compound
- auxiliary wing
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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 a kind of composite wing cargo aircraft of compound auxiliary wing of twin screw thrust, and the no compound rotor aircraft of back pressure formula includes body, is fixedly mounted on body two sides hybrid lift wing, shipping storehouse；Wherein, 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；The front end of the compound auxiliary wing of airscrew thrust self energizing is provided with screw propeller, the compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed ducted fan, the one or both sides of the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and be flexibly connected by wing hinge with hybrid lift wing, 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, low energy consumption for flight, the hang time is long, highly-safe the features such as, the auxiliary wing uses hybrid lift, it is ensured that the adaptation range of power.
Description
Technical field
The present invention relates to a kind of aircraft, the composite wing cargo aircraft of specifically a kind of compound auxiliary wing of twin screw thrust
, belong 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 the compound rotor aircraft of no back pressure formula, be assemblied in the spiral shell of its wing two sides
Revolve the compound auxiliary wing of paddle thrust self energizing and shipping storehouse composition；Wherein, the no compound rotor aircraft of back pressure formula include body,
It is fixedly mounted on body two sides hybrid lift wing；Wherein, wherein the body is set as deck platform；Described is compound
Self-enclosed ducted fan built in lifting wing, the outside design of hybrid lift wing have wing hinge；The airscrew thrust is certainly
The front end for energizing the compound auxiliary wing is provided with screw propeller, and being internally provided with for the compound auxiliary wing of airscrew thrust self energizing is self-styled
Ducted fan is closed, the one or both sides of the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and
It is flexibly connected by wing hinge with hybrid lift wing, wherein the electro-hydraulic gas interface has lid, the propeller
The 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 airscrew thrust certainly
Energize the front and back of the compound auxiliary wing；One self-enclosed ducted fan is at least installed inside the auxiliary wing of lift.Shipping storehouse is mounted on machine
The lower section of body.
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；The 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（It is taper connection with magnetic-type self interlocking interface female.
Further, hybrid lift wing can be divided into lift main wing and balance two parts of empennage, be separately positioned on compound
The front and back of lifting wing；It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space；Its
In, a self-enclosed ducted fan is at least installed inside lift main wing.
Further, body is installed with cavity, and installation diagram passes, flies the modules such as control, driving in cavity.
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, the power device is screw propeller.
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. 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.
7. 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.
8. thrust device modularization can very easily realize maintenance replacement.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, the auxiliary wing and hybrid lift aircraft are realized
Energy intercommunication between main plane, and the control by hybrid lift aircraft is acted, improve 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 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；107：Energy Management System；1021：Lift main wing；1022：The horizontal lifting rudder wing；1023：Balance empennage；1028：Wing
Hinge；1001：Socket；1002：Cavity；1003：Fixation hole；1006：Battery/fuel；108：Video camera；1026：It is magnetic-type from
Move mutual lock interface male connector；1027：Magnetic-type self interlocking interface female；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；113, shipping storehouse.
Specific embodiment
The present invention will be further described with reference to the accompanying drawing.
As shown in Figures 1 to 5, the composite wing cargo aircraft of the compound auxiliary wing of a kind of twin screw thrust, by no back pressure
The compound auxiliary wing of the compound rotor aircraft of formula, the airscrew thrust self energizing for being assemblied in its wing two sides and shipping storehouse 113 form；Its
In, the no compound rotor aircraft of back pressure formula includes body 101, is fixedly mounted on 101 two sides hybrid lift wing of body
102；Wherein, wherein the body 101 is set as deck platform；Self-enclosed duct built in the hybrid lift wing 102
Fan 104, design has wing hinge (1028) on the outside of hybrid lift wing 102；The airscrew thrust self energizing is compound auxiliary
The front end of the wing is provided with screw propeller 1062, and the compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed duct
The one or both sides of fan 104, the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface 1036 and wing hinge
(1028), it and by wing hinge (1028) is flexibly connected with hybrid lift wing 102, wherein the electro-hydraulic gas interface
1036 have lid 10361, and the compound auxiliary wing of the airscrew thrust self energizing can be divided into the auxiliary wing 10311 of lift and balance is auxiliary
10,312 two parts of empennage, are separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing；In the auxiliary wing 10311 of lift
Portion is at least equipped with a self-enclosed ducted fan 104.Shipping storehouse 113 is mounted on the lower section of body 101.
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,
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.
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.
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, the power device is screw propeller.
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 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. 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.
7. 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.
8. thrust device modularization can very easily realize maintenance replacement.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, the auxiliary wing and hybrid lift aircraft are realized
Energy intercommunication between main plane, and the control by hybrid lift aircraft is acted, improve 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 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 (7)
1. a kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust, which is characterized in that compound by no back pressure formula
The compound auxiliary wing of rotor aircraft, the airscrew thrust self energizing for being assemblied in its wing two sides, shipping storehouse（113）Composition；
Wherein, the no compound rotor aircraft of back pressure formula includes body（101）, be fixedly mounted on body（101）Two sides are multiple
Close lifting wing（102）；Wherein, wherein the body（101）It is set as deck platform；The hybrid lift wing
（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside design has wing hinge (1028)；
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 described airscrew thrust confession
The compound auxiliary wing of energy can be divided into the auxiliary wing of lift（10311）And the auxiliary empennage of balance（10312）Two parts, are separately positioned on propeller
The front and back of the compound auxiliary wing of thrust self energizing；The auxiliary wing of lift（10311）Inside is at least equipped with a self-enclosed ducted fan
（104）；
The shipping storehouse（113）It is mounted on body（101）Lower section.
2. a kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, feature exist
In the hybrid lift wing（102）Front and back are respectively set to magnetic-type self interlocking interface male connector（1026）And magnetic
Formula self interlocking interface female（1027）；The magnetic-type self interlocking interface male connector（1026）With magnetic-type automatic mutual interlocking
Mouth female（1027）Size is identical.
3. a kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust according to claim 3, which is characterized in that
The magnetic-type self interlocking interface male connector（1026）With magnetic-type self interlocking interface female（1027）For taper connection.
4. a kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, feature exist
In the hybrid lift wing（102）Lift main wing can be divided into（1021）And balance empennage（1023）Two parts, respectively
It is arranged in hybrid lift wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between be reserved with space,
The horizontal lifting rudder wing is provided in space（1022）；Wherein, lift main wing（1021）Inside is at least equipped with a self-enclosed culvert
Road fan（104）.
5. a kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, feature exist
In the body（101）It is installed with cavity（1002）, cavity（1002）Interior installation diagram passes, flies the modules such as control, driving.
6. a kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, feature exist
In being additionally provided with engine installation position on the compound auxiliary wing of the airscrew thrust self energizing（111）, engine installation position
（111）It is inside provided with power device, the power device is screw propeller.
7. a kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, feature exist
In 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 |
|---|---|---|---|
| CN201810551182.XA CN108839796A (en) | 2018-05-31 | 2018-05-31 | A kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810551182.XA CN108839796A (en) | 2018-05-31 | 2018-05-31 | A kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108839796A true CN108839796A (en) | 2018-11-20 |
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ID=64211140
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810551182.XA Pending CN108839796A (en) | 2018-05-31 | 2018-05-31 | A kind of composite wing cargo aircraft of the compound auxiliary wing of twin screw thrust |
Country Status (1)
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935512A (en) * | 2014-05-12 | 2014-07-23 | 马轶 | High endurable multi-rotor craft |
| CN205131644U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Four -axis glide vehicle |
| 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 CN201810551182.XA patent/CN108839796A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103935512A (en) * | 2014-05-12 | 2014-07-23 | 马轶 | High endurable multi-rotor craft |
| CN205131644U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Four -axis glide vehicle |
| CN107813929A (en) * | 2016-09-11 | 2018-03-20 | 郎风 | Combined type dalta wing duct aircraft |
| 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 |
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Application publication date: 20181120 |
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