CN108750089A - A kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust - Google Patents
A kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust Download PDFInfo
- Publication number
- CN108750089A CN108750089A CN201810551174.5A CN201810551174A CN108750089A CN 108750089 A CN108750089 A CN 108750089A CN 201810551174 A CN201810551174 A CN 201810551174A CN 108750089 A CN108750089 A CN 108750089A
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- wing
- compound
- lift
- auxiliary wing
- self
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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 compound rotor aircraft of the compound auxiliary wing of twin screw thrust, is made of no compound rotor aircraft of back pressure formula and the compound auxiliary wing of airscrew thrust self energizing for being assemblied in its wing both sides；The no compound rotor aircraft of back pressure formula includes body, is fixedly mounted on body both sides hybrid lift wing；Body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, hybrid lift wing outside are designed with wing hinge；The front end of the compound auxiliary wing of airscrew thrust self energizing is provided with screw propeller, is reserved with space between the auxiliary wing of lift and the auxiliary empennage of balance, the horizontal lifting rudder wing is provided in space；At least there are one self-enclosed ducted fans for installation inside the auxiliary wing of lift.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, safe the features such as, the auxiliary wing uses hybrid lift, it is ensured that the accommodation of power.
Description
Technical field
The present invention relates to a kind of aircraft, the compound rotor aircraft of specifically a kind of compound auxiliary wing of twin screw thrust belongs to
In 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 is by no compound rotor aircraft of back pressure formula and the spiral shell for being assemblied in its wing both sides
Revolve the compound auxiliary wing composition of paddle thrust self energizing；Wherein, the no compound rotor aircraft of back pressure formula includes body, is fixedly mounted
In body both sides hybrid lift wing；Wherein, wherein the body is set as deck platform；The hybrid lift wing
Built-in self-enclosed ducted fan, hybrid lift wing outside are designed with wing hinge；The airscrew thrust self energizing is compound
The front end of the auxiliary wing is provided with screw propeller, and the compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed duct wind
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 pass through wing
Hinge is flexibly connected with hybrid lift wing, wherein the electro-hydraulic gas interface carries lid, airscrew thrust confession
The compound auxiliary wing of energy can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance, and it is compound to be separately positioned on airscrew thrust self energizing
The front and back of the auxiliary wing；It is reserved with space between the auxiliary wing of lift and the auxiliary empennage of balance, the horizontal lifting rudder wing is provided in space；Its
In, at least there are one self-enclosed ducted fans for installation inside the auxiliary wing of lift.
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 two parts of lift main wing and balance 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, at least there are one self-enclosed ducted fans for installation 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 plant, the power plant is screw propeller.
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. 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；
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；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：Mounting 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.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
As shown in Figures 1 to 5, the compound rotor aircraft of the compound auxiliary wing of a kind of twin screw thrust, is answered by no back pressure formula
The compound auxiliary wing composition of airscrew thrust self energizing for closing rotor aircraft and being assemblied in its wing both sides；Wherein, the no pusher
The compound rotor aircraft of power formula includes body 101, is fixedly mounted on 101 both sides hybrid lift wing 102 of body；Wherein, wherein institute
The body 101 stated is set as deck platform；Self-enclosed ducted fan 104 built in the hybrid lift wing 102, hybrid lift
102 outside of wing is designed with wing hinge (1028)；The front end of the compound auxiliary wing of the airscrew thrust self energizing is provided with spiral shell
Paddle propeller 1062 is revolved, the compound auxiliary wing of airscrew thrust self energizing is internally provided with self-enclosed ducted fan 104, and propeller pushes away
The one or both sides of the compound auxiliary wing of power self energizing are provided with electro-hydraulic gas interface 1036 and wing hinge (1028), and are cut with scissors by wing
Chain (1028) is flexibly connected with hybrid lift wing 102, wherein the electro-hydraulic gas interface 1036 carries lid 10361, described
The compound auxiliary wing of airscrew thrust self energizing can be divided into the auxiliary wing 10311 of lift and auxiliary 10,312 two parts of empennage of balance, respectively
It is arranged in the front and back of the compound auxiliary wing of airscrew thrust self energizing；It is reserved between the auxiliary wing 10311 of lift and the auxiliary empennage 10312 of balance
There is space, the horizontal lifting rudder wing 1022 is provided in space；Wherein, at least there are one self-styled for installation inside the auxiliary wing of lift 10311
Close ducted fan 104.
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, at least there are one self-enclosed for installation inside lift main wing 1021
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 plant is provided in engine installation position 111, the power plant 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, 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. 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 should all belong to the scope of the present invention.
Claims (7)
1. a kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust, which is characterized in that flown by no back pressure formula composite wing
Row device and the compound auxiliary wing composition of the airscrew thrust self energizing for being assemblied in its wing both sides；
Wherein, the no compound rotor aircraft of back pressure formula includes body（101）, be fixedly mounted on body（101）Both 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 is designed with 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
Both sides are provided with electro-hydraulic gas interface（1036）With wing hinge (1028), and pass through wing hinge (1028) and hybrid lift wing
（102）Flexible connection, 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）With the auxiliary empennage of balance（10312）Between be reserved with space,
The horizontal lifting rudder wing is provided in space（1022）；Wherein, the auxiliary wing of lift（10311）There are one self-enclosed culverts for internal at least installation
Road fan（104）.
2. a kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, which is characterized in that institute
The hybrid lift wing stated（102）Front and back are respectively set to magnetic-type self interlocking interface male connector（1026）With it is magnetic-type automatic
Mutual lock interface female（1027）；The magnetic-type self interlocking interface male connector（1026）With magnetic-type self interlocking interface female
（1027）Size is identical.
3. a kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust according to claim 3, which is characterized in that institute
The magnetic-type self interlocking interface male connector stated（1026）With magnetic-type self interlocking interface female（1027）For taper connection.
4. a kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, which is characterized in that institute
The hybrid lift wing stated（102）Lift main wing can be divided into（1021）And balance empennage（1023）Two parts, are respectively set
In hybrid lift wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between be reserved with space, space
Inside it is provided with the horizontal lifting rudder wing（1022）；Wherein, lift main wing（1021）There are one self-enclosed duct wind for internal at least installation
Fan（104）.
5. a kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, which is characterized in that institute
The body stated（101）It is installed with cavity（1002）, cavity（1002）Interior installation diagram passes, flies the modules such as control, driving.
6. a kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, which is characterized in that institute
It is additionally provided with engine installation position on the compound auxiliary wing of airscrew thrust self energizing stated（111）, engine installation position（111）Inside set
It is equipped with power plant, the power plant is screw propeller.
7. a kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust according to claim 1, which is characterized in that institute
It is provided with battery/fuel on the compound auxiliary wing of airscrew thrust self energizing stated（1006）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810551174.5A CN108750089A (en) | 2018-05-31 | 2018-05-31 | A kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810551174.5A CN108750089A (en) | 2018-05-31 | 2018-05-31 | A kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108750089A true CN108750089A (en) | 2018-11-06 |
Family
ID=64001256
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810551174.5A Pending CN108750089A (en) | 2018-05-31 | 2018-05-31 | A kind of compound rotor aircraft of the compound auxiliary wing of twin screw thrust |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108750089A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111204444A (en) * | 2020-03-17 | 2020-05-29 | 中国科学院工程热物理研究所 | Wing tip connecting structure of combined unmanned aerial vehicle |
| CN114348240A (en) * | 2020-10-14 | 2022-04-15 | 保时捷股份公司 | Ducted propeller of aircraft and aircraft |
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| 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 |
| CA2677508A1 (en) * | 2008-09-03 | 2010-03-03 | Anvar Ismailov | Unmanned air vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111204444A (en) * | 2020-03-17 | 2020-05-29 | 中国科学院工程热物理研究所 | Wing tip connecting structure of combined unmanned aerial vehicle |
| CN114348240A (en) * | 2020-10-14 | 2022-04-15 | 保时捷股份公司 | Ducted propeller of aircraft and aircraft |
| CN114348240B (en) * | 2020-10-14 | 2023-10-31 | 保时捷股份公司 | Ducted propeller of aircraft and aircraft |
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Application publication date: 20181106 |
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