CN108466691A - The compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan - Google Patents
The compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan Download PDFInfo
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- CN108466691A CN108466691A CN201810544200.1A CN201810544200A CN108466691A CN 108466691 A CN108466691 A CN 108466691A CN 201810544200 A CN201810544200 A CN 201810544200A CN 108466691 A CN108466691 A CN 108466691A
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- wing
- ducted fan
- compound
- rotor aircraft
- rear single
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- 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
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The present invention is a kind of compound rotor aircraft of rear single ducted fan formula of the compound auxiliary wing of double ducted fans, is made of rear single compound rotor aircraft of ducted fan formula and the compound auxiliary wing of ducted fan thrust self energizing for being assemblied in its both sides；Wherein, rear single compound rotor aircraft of ducted fan formula includes body, is fixedly mounted on body both sides hybrid lift wing, screw propeller；Wherein, body is set as deck platform；Self-enclosed ducted fan built in hybrid lift wing, hybrid lift wing outside are designed with wing hinge；Self-enclosed ducted fan is provided in the compound auxiliary wing of ducted fan thrust self energizing, the one or both sides of the compound auxiliary wing of ducted fan thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and are flexibly connected with hybrid lift wing by wing hinge.The present invention not only has landing apart from short, flying speed is fast, wing structure intensity is high, wing can with energy storage, flight low energy consumption, the hang time is long the features such as, the hybrid lift wing of large area, it can play the role of aerodone under case of emergency, greatly improve the safety of aircraft, the safety of support personnel and goods and materials.
Description
Technical field
The present invention relates to a kind of aircraft, rear single ducted fan formula of specifically a kind of double compound auxiliary wings of ducted fan is multiple
Rotor aircraft is closed, aircraft equipment technology field is belonged to.
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
Controllability when flat flight is not satisfactory, and that there is flight resistances is big, energy consumption is high, blade is easy to hurt sb.'s feelings, is easy on the outside of blade
It damages, the shortcomings of 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.Ducted fan
More can be well protected propelling screws, at the same also ensured personnel up and down aircraft when safety, and improve propeller
Efficiency.
To achieve the goals above, a kind of rear single ducted fan formula composite wing of double compound auxiliary wings of ducted fan of the present invention flies
Row device, it is compound auxiliary by rear single compound rotor aircraft of ducted fan formula and the ducted fan thrust self energizing for being assemblied in its wing both sides
The wing forms；Wherein, rear single compound rotor aircraft of ducted fan formula includes body, is fixedly mounted on the compound liter in body both sides
Power wing, propeller；Wherein, body is set as deck platform；Self-enclosed ducted fan, hybrid lift built in hybrid lift wing
It is designed with wing hinge on the outside of wing；Propeller is ducted fan propeller；Before the compound auxiliary wing of ducted fan thrust self energizing
End is provided with ducted fan propeller, and the compound auxiliary wing of ducted fan thrust self energizing is internally provided with self-enclosed ducted fan,
The one or both sides of the compound auxiliary wing of ducted fan thrust self energizing are provided with electro-hydraulic gas interface and wing hinge, and are cut with scissors by wing
Chain is flexibly connected with hybrid lift wing；The compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing of lift and the auxiliary tail of balance
Two parts of the wing, the front and back for being separately positioned on the compound auxiliary wing of no thrust self energizing wherein, are at least equipped with inside the auxiliary wing of lift
One self-enclosed ducted fan.
Further, hybrid lift wing can be divided into two parts of lift main wing and balance empennage, be separately positioned on compound
Lifting wing front and back；Lift main wing）It is reserved with space between balance empennage, the horizontal lifting rudder wing is provided in space；Its
In, at least there are one self-enclosed ducted fans for installation inside lift main wing.
Further, further include vertical tail, the vertical tail is arranged above or below body；The vertical tail is set
It sets in wing both sides；The vertical tail may be implemented to fold；Mobilizable vertical rudder wing is installed behind the vertical tail.
Further, the vertical rudder wing is movably connected in the rear of vertical tail,.
Further, vertical tail, forms an angle with body planar shaped, and haulage gear is equipped on vertical tail, realizes vertical
The deflection of the rudder wing.
Further, body is set as deck platform；The mounting hole of the regular arrangement in deck platform both sides；The first
It is designed with socket on plate platform；The socket is female or male.
Further, electro-hydraulic gas interface carries lid.
Further, it is provided with video camera in front of body, video camera is monopod video camera.
Further, it is provided with battery/fuel on the compound auxiliary wing of ducted fan thrust self energizing.
The prior art is compared, the main feature having is invented：
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, wing
It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight
Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated
Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously
The safety of row device has ensured the safety of personnel and goods and materials.
3, the present invention can realize multiple functions using hardware and software platform, modularized design,
4, the present invention using both sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
6. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable input of client, reduces buying and operation cost.
7. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the present invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, it is synchronous to be controlled by hybrid lift aircraft main control unit, it expands again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
8. thrust device modularization can very easily realize that repair is replaced.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift aircraft
Energy intercommunication between main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
10. aerofoil type energy device, efficiently uses space.
11. 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；106：Propeller；107：Energy Management System；1021：Lift main wing；1022：The horizontal lifting rudder wing；1023：Balance tail
The wing；1028：Wing hinge；1001：Socket；1002：Cavity；1003：Mounting hole；1006：Battery/fuel；10311, lift is auxiliary
The wing；10312, auxiliary empennage is balanced；1036, electro-hydraulic gas interface；10361, lid；108, video camera；；1063, ducted fan promotes
Device.
Specific implementation mode
The present invention will be further described below in conjunction with the accompanying drawings.
As shown in Figure 1, a kind of compound rotor aircraft of rear single ducted fan formula of compound auxiliary wing of double ducted fans, feature exist
In by rear single compound rotor aircraft of ducted fan formula and being assemblied in the compound auxiliary wing of ducted fan thrust self energizing of its wing both sides
Composition；Wherein, described rear single compound rotor aircraft of ducted fan formula includes body 101, to be fixedly mounted on 101 both sides of body multiple
Close lifting wing 102, propeller 106；Wherein, the body 101 is set as deck platform；The hybrid lift wing
Self-enclosed ducted fan 104 built in 102,102 outside of hybrid lift wing are designed with wing hinge 1028；The propeller
106 be ducted fan propeller；The front end of the compound auxiliary wing of ducted fan thrust self energizing is provided with ducted fan propulsion
Device 1063, the compound auxiliary wing of ducted fan thrust self energizing are internally provided with self-enclosed ducted fan 104, and ducted fan thrust is certainly
The one or both sides for energizing the compound auxiliary wing are provided with electro-hydraulic gas interface 1036 and wing hinge 1028, and pass through wing hinge 1028
It is flexibly connected with hybrid lift wing 102；The compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing 10311 of lift and put down
It weighs 10,312 two parts of auxiliary empennage, is separately positioned on the front and back of the compound auxiliary wing of no thrust self energizing wherein, the auxiliary wing of lift
At least there are one self-enclosed ducted fans 104 for installation inside 10311.
As further improvement of the invention, hybrid lift wing 102 can be divided into lift main wing 1021 and balance empennage
1023 two parts, are separately positioned on the front and back of hybrid lift wing 102；Between lift main wing 1021 and balance empennage 1023
It is reserved with space, the horizontal lifting rudder wing 1022 is provided in space；Wherein, at least there are one certainly for installation inside lift main wing 1021
Close ducted fan 104.
Further include vertical tail 105 as further improvement of the invention, the vertical tail 105 is arranged in body 101
Above or below；The vertical tail 105 is arranged in wing both sides；The vertical tail 105 may be implemented to fold；It is described vertical
Mobilizable vertical rudder wing 1051 is installed behind empennage 105.
As further improvement of the invention, the vertical rudder wing 1051 is movably connected in the rear of vertical tail, 105.
As further improvement of the invention, vertical tail, 105 forms an angle with body planar shaped, and is installed on vertical tail,
There is haulage gear, realizes the deflection of the vertical rudder wing.
As further improvement of the invention, body 101 is set as deck platform；The deck platform both sides are regular
The mounting hole 1003 of arrangement；Socket 1001 is designed in the deck platform；The socket 1001 is female or male.
As further improvement of the invention, electro-hydraulic gas interface 1036 carries lid 10361.
As further improvement of the invention, 101 front of body is provided with video camera 108, and video camera 108 is that holder images
Machine.
As further improvement of the invention, battery/fuel is provided on the compound auxiliary wing of ducted fan thrust self energizing
1006。
The prior art is compared, the main feature having is invented：
1, the present invention has landing apart from short, and flying speed is fast, maneuverability, avoidance ability are strong, wing structure intensity is high, wing
It can be with energy storage, the features such as low energy consumption of flying.It relies on self-enclosed vertical ducted fan, aircraft can be provided in horizontal flight
Additional maneuverability realizes the super maneuver ability of moment change of flight posture and track.
2, the very large Waverider wing of the present invention, can play the role of certain paraglider, substantially reduce acceleration of gravity,
Safety coefficient is greatly improved, the control function of the hydroplane wing and the vertical rudder wing and the aerofoil closing of self-enclosed ducted fan are coordinated
Function greatly improves winged even if lift ducted fan and horizontal propeller can realize that aerodone formula is force-landed if damage simultaneously
The safety of row device has ensured the safety of personnel and goods and materials.
3, the present invention can realize multiple functions using hardware and software platform, modularized design,
4, the present invention using both sides wing can Expanding design, wing area can be expanded when necessary, improve the standard flight when
Lift, improve load capacity.
5, the present invention also has successive socket, and the cluster of aircraft is facilitated to fly, and further decreases cluster flight
When power consumption.In front and back serial connection, the aircraft at rear only needs a small amount of energy expenditure, can be achieved with flying for long range
Row, not the cluster flight of only aircraft provide the low-power consumption scheme of clustering, it might even be possible to realize the sky between aircraft
Middle rescue, i.e., before aircraft the dragging of faulty aircraft below is taken off, realize and mutually come to sb.'s rescue between aircraft not seen before
Help phenomenon.
6. can pass through between the auxiliary wing of modularization ducted fan drive-in hybrid lift and hybrid lift aircraft of invention
Wing hinge and electro-hydraulic gas interface are attached, and are controlled by hybrid lift aircraft main control unit, and can be by battery/combustion of aerofoil
The energy transmissions such as material give aircraft host, improve the flight time.The multiplication of performance may be implemented by the auxiliary wing of superimposion lift.
Modular design reduces the disposable input of client, reduces buying and operation cost.
7. the modularization auxiliary wing of ducted fan drive-in hybrid lift of the present invention is in parallel with the auxiliary wing of other hybrid lifts,
And be attached by wing hinge and electro-hydraulic gas interface, it is synchronous to be controlled by hybrid lift aircraft main control unit, it expands again
And the energy transmissions such as battery/fuel of aerofoil can be given to aircraft host, improve the flight time.
8. thrust device modularization can very easily realize that repair is replaced.
9. in the present invention, auxiliary wing one or both sides are provided with electro-hydraulic gas interface, realize the auxiliary wing and hybrid lift aircraft
Energy intercommunication between main plane, and action is controlled by hybrid lift aircraft, improves the flexibility of complete machine.
10. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
11. aerofoil type energy device, efficiently uses space.
12. the present invention uses modularized design, compound different types of machines to use, cost has been saved.
Schematically the present invention and embodiments thereof are described above, description is not limiting, institute in attached drawing
What is shown is also one of embodiments of the present invention, and actual structure is not limited to this.So if the common skill of this field
Art personnel are enlightened by it, without departing from the spirit of the invention, are not inventively designed and the technical solution
Similar frame mode and embodiment, are within the scope of protection of the invention.
Claims (9)
1. a kind of compound rotor aircraft of rear single ducted fan formula of compound auxiliary wing of double ducted fans, which is characterized in that by rear Dan Han
The compound rotor aircraft of road fan-type and the compound auxiliary wing composition of the ducted fan thrust self energizing for being assemblied in its wing both sides；
Wherein, rear single compound rotor aircraft of ducted fan formula includes body（101）, be fixedly mounted on body（101）Two
Side hybrid lift wing（102）, propeller（106）；Wherein, the body（101）It is set as deck platform；Described is compound
Lifting wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside is designed with wing hinge
(1028)；The propeller（106）For ducted fan propeller；
The front end of the compound auxiliary wing of ducted fan thrust self energizing is provided with ducted fan propeller（1063）, ducted fan
The compound auxiliary wing of thrust self energizing is internally provided with self-enclosed ducted fan（104）, the compound auxiliary wing of ducted fan thrust self energizing
One or both sides be provided with electro-hydraulic gas interface（1036）With wing hinge (1028), and by wing hinge (1028) with it is compound
Lifting wing（102）Flexible connection；The compound auxiliary wing of ducted fan thrust self energizing can be divided into the auxiliary wing of lift（10311）And balance
Auxiliary empennage（10312）Two parts are separately positioned on the front and back of the compound auxiliary wing of no thrust self energizing wherein, the auxiliary wing of lift
（10311）There are one self-enclosed ducted fans for internal at least installation（104）.
2. a kind of compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan according to claim 1,
It is characterized in that, the hybrid lift wing（102）Lift main wing can be divided into（1021）And balance empennage（1023）Two
Part is separately positioned on hybrid lift wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between it is pre-
There are space, the horizontal lifting rudder wing is provided in space（1022）；Wherein, lift main wing（1021）There are one internal at least installations
Self-enclosed ducted fan（104）.
3. a kind of compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan according to claim 1,
It is characterized in that, further including vertical tail（105）, the vertical tail（105）It is arranged in body（101）Above or below；Institute
State vertical tail（105）It is arranged in wing both sides；The vertical tail（105）It may be implemented to fold；The vertical tail（105）
Mobilizable vertical rudder wing is installed below（1051）.
4. a kind of compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan according to claim 3,
It is characterized in that, the vertical rudder wing（1051）It is movably connected in vertical tail,（105）Rear.
5. a kind of compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan according to claim 3,
It is characterized in that, the vertical tail,（105）It forms an angle with body planar shaped, and haulage gear is installed on vertical tail,
Realize the deflection of the vertical rudder wing.
6. a kind of compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan according to claim 1,
It is characterized in that, the body（101）It is set as deck platform；The mounting hole of the regular arrangement in deck platform both sides
（1003）；It is designed with socket in the deck platform（1001）；The socket（1001）For female or male.
7. a kind of compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan according to claim 1,
It is characterized in that, the electro-hydraulic gas interface（1036）With lid（10361）.
8. a kind of compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan according to claim 1,
It is characterized in that, the body（101）Front is provided with video camera（108）；Video camera（108）For monopod video camera.
9. a kind of compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan according to claim 1,
It is characterized in that, being provided with battery/fuel on the compound auxiliary wing of ducted fan thrust self energizing（1006）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544200.1A CN108466691A (en) | 2018-05-31 | 2018-05-31 | The compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810544200.1A CN108466691A (en) | 2018-05-31 | 2018-05-31 | The compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan |
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| Publication Number | Publication Date |
|---|---|
| CN108466691A true CN108466691A (en) | 2018-08-31 |
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ID=63261664
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810544200.1A Pending CN108466691A (en) | 2018-05-31 | 2018-05-31 | The compound rotor aircraft of rear single ducted fan formula of double compound auxiliary wings of ducted fan |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109552618A (en) * | 2018-12-01 | 2019-04-02 | 江苏鸿鹄无人机应用科技有限公司 | A kind of unmanned plane emergency back-up flight device |
-
2018
- 2018-05-31 CN CN201810544200.1A patent/CN108466691A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109552618A (en) * | 2018-12-01 | 2019-04-02 | 江苏鸿鹄无人机应用科技有限公司 | A kind of unmanned plane emergency back-up flight device |
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Application publication date: 20180831 |