CN108502168A - The rear compound rotor aircraft of single-blade folding with the compound auxiliary wing of airscrew thrust - Google Patents
The rear compound rotor aircraft of single-blade folding with the compound auxiliary wing of airscrew thrust Download PDFInfo
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- CN108502168A CN108502168A CN201810550505.3A CN201810550505A CN108502168A CN 108502168 A CN108502168 A CN 108502168A CN 201810550505 A CN201810550505 A CN 201810550505A CN 108502168 A CN108502168 A CN 108502168A
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- 150000001875 compounds Chemical class 0.000 title claims abstract description 57
- 239000002131 composite material Substances 0.000 claims abstract description 7
- 238000009434 installation Methods 0.000 claims description 16
- 239000000446 fuel Substances 0.000 claims description 6
- 238000010586 diagram Methods 0.000 claims description 4
- 238000005265 energy consumption Methods 0.000 abstract description 7
- 238000004146 energy storage Methods 0.000 abstract description 4
- 230000006872 improvement Effects 0.000 description 7
- 230000005540 biological transmission Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 230000001133 acceleration Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The present invention is a kind of hybrid lift aircraft of band expansion platform, is made of rear single-screw paddle composite wing aircraft and the compound auxiliary wing of airscrew thrust self energizing for being assemblied in its both sides；Wherein, rear single-screw paddle composite wing aircraft include body, it is foldable be 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 airscrew thrust self energizing, 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 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, the auxiliary wing using hybrid lift, the auxiliary wing with propeller power, low energy consumption for flight, the hang time is long, safe the features such as.
Description
Technical field
The present invention relates to a kind of aircraft, specifically a kind of rear single-blade folding with the compound auxiliary wing of airscrew thrust 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
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.
To achieve the goals above, the present invention includes rear single-screw paddle composite wing aircraft, is movably arranged on compound liter
The compound auxiliary wing of airscrew thrust self energizing of power aircraft both sides；Wherein, rear single-screw paddle composite wing aircraft include body,
It is foldable to be mounted on body both sides hybrid lift wing, screw propeller；Wherein, body is set as deck platform；Compound liter
Self-enclosed ducted fan built in power wing, hybrid lift wing outside are designed with wing hinge；Airscrew thrust self energizing is compound
Self-enclosed ducted fan is provided in the auxiliary wing, 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 compound auxiliary wing of airscrew thrust self energizing
One or both sides are provided with electro-hydraulic gas interface and wing hinge, and are flexibly connected with hybrid lift wing by wing hinge,
In, electro-hydraulic gas interface carries lid.
Further, hybrid lift wing is mounted on body both sides by the way that folding hinge is folding.
Further, propeller is a variety of dynamic structures such as electric propeller, the dynamic propeller of oil.
Further, hybrid lift wing front and back are respectively set to magnetic-type self interlocking interface male connector and magnetic-type automatic
Mutual lock interface female；Magnetic-type self interlocking interface male connector is identical as magnetic-type self interlocking interface female size.
Further, magnetic-type self interlocking interface male connector and magnetic-type self interlocking interface female are taper connection
Further, hybrid lift wing can be divided into two parts of lift main wing and balance empennage, be separately positioned on hybrid lift
The front and back of wing；It is reserved with space between lift main wing and balance empennage, the horizontal lifting rudder wing is provided in space；Wherein,
At least there are one self-enclosed ducted fans for installation inside lift main wing.
Further, further include vertical tail, the vertical tail is arranged above or below body；The vertical tail is set
It sets in wing both sides；The vertical tail may be implemented to fold；Mobilizable vertical rudder wing is installed behind the vertical tail.
Further, body is installed with cavity, and installation diagram passes, flies the modules such as control, driving in cavity..
Further, the compound auxiliary wing of airscrew thrust self energizing can be divided into the auxiliary wing of lift and auxiliary two parts of empennage of balance,
It is separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing；It is reserved between the auxiliary wing of lift and the auxiliary empennage of balance free
Between, the horizontal lifting rudder wing is provided in space；Wherein, at least there are one self-enclosed ducted fans for installation inside the auxiliary wing of lift.
Further, it is additionally provided with engine installation position and battery/fuel on the compound auxiliary wing of airscrew thrust self energizing,
In, engine is provided with power plant in installation position.
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, foldable pattern is used between body and both sides wing；Fold mechanism is folding hinge；After the wing expansion of both sides
It can locking.Occupied space when to reduce storage and transport is particularly suitable under the limited environment in the spaces such as family and aircraft carrier
It uses.Using the program, the quantity of the carrier-borne aircraft of aircraft carrier can be greatly improved.The hangar of same area, can store double
The aircraft of quantity；Or realize the advantages that quantity for the aircraft that medium-sized aircraft carrier carries is no less than large-scale aircraft carrier.
3, the auxiliary wing of modularization ducted fan drive-in hybrid lift invented uses hybrid lift, i.e., by designing in aerofoil
Interior self-enclosed ducted fan generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to form hybrid lift.
4, 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.
5, the present invention can realize multiple functions using hardware and software platform, modularized design,
6, 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.
7, 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.
8. 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.
9. 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.
10. thrust device modularization can very easily realize that repair is replaced.
In 11 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.
12. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
13. aerofoil type energy device, efficiently uses space.
14. 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；108：Video camera；
1026：Magnetic-type self interlocking interface male connector；1027：Magnetic-type self interlocking interface female；1031, airscrew thrust self energizing
The compound auxiliary wing；10311, the auxiliary wing of lift；10312, auxiliary empennage is balanced；1026, electro-hydraulic gas interface；10261, lid；111, start
Machine installation position；1059：Folding hinge；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 rear compound rotor aircraft of single-blade folding with the compound auxiliary wing of airscrew thrust, including
Afterwards single-screw paddle composite wing aircraft, be assemblied in the compound auxiliary wing of airscrew thrust self energizing of its wing both sides；Wherein, described
Rear single-screw paddle composite wing aircraft include body 101, the foldable hybrid lift wing mounted on 101 both sides of body
102, propeller 106；Wherein, the body 101 is set as deck platform；It is self-styled built in the hybrid lift wing 102
Ducted fan 104 is closed, 102 outside of hybrid lift wing is designed with wing hinge 1028；The airscrew thrust self energizing is multiple
The front end for closing the auxiliary wing is provided with screw propeller 1062, and being internally provided with for the compound auxiliary wing of airscrew thrust self energizing is self-enclosed
The one or both sides of ducted fan 104, the compound auxiliary wing of airscrew thrust self energizing are provided with electro-hydraulic gas interface 1036 and wing hinge
Chain 1028, and be flexibly connected with hybrid lift wing 102 by wing hinge 1028, wherein the electro-hydraulic gas interface 1036
With lid 10361.
As further improvement of the invention, hybrid lift wing 102 is mounted on by the way that folding hinge 1059 is folding
101 both sides of body.
As further improvement of the invention, propeller 106 is screw propeller；The propeller 106 is electronic
A variety of dynamic structures such as the dynamic propeller of propeller, oil.
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.
Further include vertical tail 105 as further improvement of the invention, the vertical tail 105 is arranged in body 101
Above or below；The vertical tail 105 is arranged in wing both sides；The vertical tail 105 may be implemented to fold；It is described vertical
Mobilizable vertical rudder wing 1051 is installed behind empennage 105.
Improved as of the invention further, body 101 is installed with cavity 1002, in cavity 1002 installation diagram pass, fly control,
The modules such as driving.
Improved as of the invention further, the compound auxiliary wing of airscrew thrust self energizing can be divided into the auxiliary wing of lift 10311 with
And auxiliary 10,312 two parts of empennage of balance, it is separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing；The auxiliary wing of lift
It is reserved with space between 10311 and the auxiliary empennage of balance 10312, the horizontal lifting rudder wing 1022 is provided in space；Wherein, lift is auxiliary
At least there are one self-enclosed ducted fans 104 for installation inside the wing 10311.
As further improvement of the invention, engine installation position is additionally provided on the compound auxiliary wing of airscrew thrust self energizing
111 and battery/fuel 1006, wherein be provided with power plant in the engine installation position 111.
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, foldable pattern is used between body and both sides wing；Fold mechanism is folding hinge；After the wing expansion of both sides
It can locking.Occupied space when to reduce storage and transport is particularly suitable under the limited environment in the spaces such as family and aircraft carrier
It uses.Using the program, the quantity of the carrier-borne aircraft of aircraft carrier can be greatly improved.The hangar of same area, can store double
The aircraft of quantity；Or realize the advantages that quantity for the aircraft that medium-sized aircraft carrier carries is no less than large-scale aircraft carrier.
3, the auxiliary wing of modularization ducted fan drive-in hybrid lift invented uses hybrid lift, i.e., by designing in aerofoil
Interior self-enclosed ducted fan generates the lift that lift and the auxiliary wing of lift are generated in horizontal flight, to form hybrid lift.
4, 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.
5, the present invention can realize multiple functions using hardware and software platform, modularized design,
6, 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.
7, 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.
8. 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.
9. 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.
10. thrust device modularization can very easily realize that repair is replaced.
In 11 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.
12. the auxiliary wing is also built-in with the horizontal lifting rudder wing, improves complete machine and manipulate agility！
13. aerofoil type energy device, efficiently uses space.
14. 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 (10)
1. the rear compound rotor aircraft of single-blade folding with the compound auxiliary wing of airscrew thrust, which is characterized in that including rear single spiral shell
The compound auxiliary wing of the compound rotor aircraft of rotary propeller type, the airscrew thrust self energizing for being assemblied in its wing both sides；
Wherein, the rear single-screw paddle composite wing aircraft includes body（101）, it is foldable be mounted on body（101）Two
The hybrid lift wing of side（102）, propeller（106）；Wherein, the body（101）It is set as deck platform；Described answers
Close lifting wing（102）Built-in self-enclosed ducted fan（104）, hybrid lift wing（102）Outside is designed with wing hinge
(1028)；Propeller（106）For screw propeller；
The 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）.
2. the rear compound rotor aircraft of single-blade folding according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the hybrid lift wing（102）Pass through folding hinge（1059）It is folding to be mounted on body（101）Two
Side.
3. the rear compound rotor aircraft of single-blade folding according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the propeller（106）For screw propeller；The propeller（106）For electric propeller, the dynamic spiral shell of oil
Revolve a variety of dynamic structures such as paddle.
4. the rear compound rotor aircraft of single-blade folding according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the hybrid lift wing（102）Front and back are respectively set to magnetic-type self interlocking interface male connector（1026）
With magnetic-type self interlocking interface female（1027）；The magnetic-type self interlocking interface male connector（1026）With it is magnetic-type automatic
Mutual lock interface female（1027）Size is identical.
5. the rear compound rotor aircraft of single-blade folding with the compound auxiliary wing of airscrew thrust described in 3 is wanted according to right, it is special
Sign is, the magnetic-type self interlocking interface male connector（1026）With magnetic-type self interlocking interface female（1027）For taper
Connection.
6. the rear compound rotor aircraft of single-blade folding according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the hybrid lift wing（102）Lift main wing can be divided into（1021）And balance empennage（1023）Two portions
Point, it is separately positioned on hybrid lift wing（102）Front and back；Lift main wing（1021）With balance empennage（1023）Between reserve
There is space, the horizontal lifting rudder wing is provided in space（1022）；Wherein, lift main wing（1021）There are one certainly for internal at least installation
Close ducted fan（104）.
7. the rear compound rotor aircraft of single-blade folding according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, further includes vertical tail（105）, the vertical tail（105）It is arranged in body（101）Above or below；It is described
Vertical tail（105）It is arranged in wing both sides；The vertical tail（105）It may be implemented to fold；The vertical tail（105）Afterwards
Face is equipped with mobilizable vertical rudder wing（1051）.
8. the rear compound rotor aircraft of single-blade folding according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the body（101）It is installed with cavity（1002）, cavity（1002）Interior installation diagram passes, flies the moulds such as control, driving
Block.
9. the rear compound rotor aircraft of single-blade folding according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, the compound auxiliary wing of the airscrew thrust self energizing can be divided into the auxiliary wing of lift（10311）And the auxiliary empennage of balance
（10312）Two parts are separately positioned on the front and back of the compound auxiliary wing of airscrew thrust self energizing；The auxiliary wing of lift（10311）With
Balance auxiliary empennage（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 ducted fans for internal at least installation（104）.
10. the rear compound rotor aircraft of single-blade folding according to claim 1 with the compound auxiliary wing of airscrew thrust,
It is characterized in that, engine installation position is additionally provided on the compound auxiliary wing of the airscrew thrust self energizing（111）With battery/fuel
（1006）, wherein the engine installation position（111）Inside it is provided with power plant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810550505.3A CN108502168A (en) | 2018-05-31 | 2018-05-31 | The rear compound rotor aircraft of single-blade folding with the compound auxiliary wing of airscrew thrust |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810550505.3A CN108502168A (en) | 2018-05-31 | 2018-05-31 | The rear compound rotor aircraft of single-blade folding with the compound auxiliary wing of airscrew thrust |
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| CN108502168A true CN108502168A (en) | 2018-09-07 |
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| Application Number | Title | Priority Date | Filing Date |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117775339A (en) * | 2024-02-28 | 2024-03-29 | 成都金支点科技有限公司 | Servo control mechanism and unmanned aerial vehicle of collapsible rudder |
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| CN203698663U (en) * | 2014-02-19 | 2014-07-09 | 厦门大学 | Ornithopter with foldable aerofoils |
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| CN205131649U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Multi -axis aircraft |
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| CN107813929A (en) * | 2016-09-11 | 2018-03-20 | 郎风 | Combined type dalta wing duct aircraft |
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