CN108238247A - A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer - Google Patents
A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer Download PDFInfo
- Publication number
- CN108238247A CN108238247A CN201810143121.XA CN201810143121A CN108238247A CN 108238247 A CN108238247 A CN 108238247A CN 201810143121 A CN201810143121 A CN 201810143121A CN 108238247 A CN108238247 A CN 108238247A
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- installation axle
- vertically taking
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- 238000006073 displacement reaction Methods 0.000 claims abstract description 12
- 238000009434 installation Methods 0.000 claims description 42
- 241000883990 Flabellum Species 0.000 claims description 6
- 125000006850 spacer group Chemical group 0.000 claims description 6
- 230000005484 gravity Effects 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 12
- 239000003921 oil Substances 0.000 description 10
- 238000010586 diagram Methods 0.000 description 7
- 238000005452 bending Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000178 monomer Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000008439 repair process Effects 0.000 description 2
- 230000003313 weakening effect Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
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- B64D27/026—
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention discloses a kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer, the aircraft includes at least two panels main rotor, main rotor one end is connect with intermediate connector, intermediate connector is connect with main rotor displacement system, in thrust device or draft gear of the end of the every main rotor equipped with driving main rotor rotation, main rotor displacement system one end is connect by intermediate connector with main rotor, the other end is connect with hollow pipe, preflow push rotor is equipped with below main rotor, the drive shaft of preflow push rotor is connect by first clutch with engine, engine is also connect by second clutch with generator, generator is electrically connected with power-supply controller of electric.The oil electric mixed dynamic active rotor vertically taking off and landing flyer have it is simple in structure, can be greatly reduced to the driving power of main rotor or the quick driving force improved to main rotor, additionally it is possible to overcome gyroscopic effect caused by main rotor the features such as torsional moment.
Description
Technical field
The present invention relates to vertically taking off and landing flyer for technical field, and in particular to a kind of oil electric mixed dynamic active rotor hangs down
Straight landing aircraft.
Background technology
It is well known that helicopter includes fuselage, the main rotor on the top at position among fuselage and for supporting
Disappear the anti torque tail rotor of the torque that fuselage is transferred to from main rotor.
Hinged main rotor and/or antitorque rotor is also known.More specifically, hinged rotor is included around the
One axis rotation drive shaft, with drive shaft integrally around first axle rotation propeller hub and from propeller hub upper edge relative to
First axle is multiple blades that each second axis of radial direction is stretched out.
Each blade can be rotated relative to propeller hub around respective second axis, to change its angle of shock relative to air-flow
Degree, and can freely be vibrated around respective third axis relative to propeller hub, to carry out so-called optimal auction.Each third axis
To the first and second Axis Cross of related blade.
Each blade is free around the respective four axistyle for being parallel to first axle also relative to propeller hub and other blades
Oscillation is moved with carrying out so-called wave (lead-lag).
Occurs such a demand in this field：In the case of the aerodynamic quality for not weakening rotor itself,
In vibration caused by a wide range of interior oscillating motion for weakening blade of the drive shaft around the rotary speed of first axle.
At present, it is to provide power by built-in motor that machine helicopter, which generates power, and common engine type has fuel oil hair
Rotary power is supplied to a kind of upright parallel shaft by motivation, cylinder piston type engine or turbo type engine, engine, should
The propeller of output terminal one connection, six monomers of upright parallel shaft, has horizontally rotated the propeller blade of six monomers
Come, in this way, propeller blade cuts its top still air, the still air after being cut just produces a sky to flow downward
Air-flow generates propeller upward lift with Airflow, under the action of such active force and reaction force, helicopter
It goes up aerial.
The power of existing lifting airscrew, will by vertically taking off and landing flyer main rotor displacement system all only by engine
Power sends main rotor to, and since the main rotor of helicopter is longer, the required torque of customer service air drag also can be very
Greatly.
Invention content
It is an object of the invention to overcome defect in the prior art, provide it is a kind of it is simple in structure, can be greatly reduced
Driving force or the quick driving force improved to main rotor to main rotor, additionally it is possible to gyroscopic effect be overcome to be turned round caused by main rotor
A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer of torque.
To achieve the above object, the technical scheme is that designing a kind of oil electric mixed dynamic active rotor VTOL
Aircraft, the aircraft include at least two panels main rotor, and main rotor one end is connect with intermediate connector, intermediate connector and master
Rotary wing changing is connected away from system, in thrust device or traction dress of the end of the every main rotor equipped with driving main rotor rotation
It puts, main rotor displacement system one end is connect by intermediate connector with main rotor, and the other end is connect with hollow pipe, in main rotor
Preflow push rotor is arranged below, the drive shaft of preflow push rotor is connect by first clutch with engine, and engine is also
It is connect by second clutch with generator, generator is electrically connected with power-supply system.
Since preflow push rotor one end of the helicopter is connect with engine, thrust is also associated in the end of main rotor
Device or draft gear.Therefore when helicopter low cruise, the connection between first clutch and engine can be disconnected, only
Second clutch is connect with engine, engine drives main rotor to revolve by electrical power generators arch thrust device or draft gear
Turn, while can also be accumulator electric power storage.When helicopter needs high-performance cruise, first clutch can be connect with engine, it will
Connection between second clutch and engine disconnects, and thrust device or draft gear can be by the electric power of accumulator by leading at this time
The end driving main rotor of rotor, engine are rotated by preflow push preflow push rotor A1, thus can be significantly
The driving force of preflow push rotor A1 is improved, reaches the effect of high-performance cruise.And in low cruise, due to thrust device
Or draft gear is installed in the end of main rotor, due to the effect of lever principle, is driven in the case where output torque is identical
Power is also just smaller further away from the required thrust of rotation center, therefore can be greatly reduced defeated needed for thrust device or draft gear
Go out power, reach the effect of energy saving.
For the ease of the connection between thrust device or draft gear and main rotor end, while ensure that main rotor stress is closed
Reason, preferred technical solution are that the thrust device or draft gear pass through the installation axle for being arranged on main rotor end and main rotation
It is rotatablely connected between the wing, and the axis of installation axle is overlapped with the transverse axis of main rotor or parallel, the thrust device or traction
The thrust direction of device with the direction of rotation of main rotor on the contrary, and it is vertical with the axis direction of installation axle, in the thrust device
Or the side of draft gear is fixedly connected with orientation fin, orients and is symmetrical with thrust device between fin and every main rotor end
Or the axis of draft gear, orientation fin are used to make the center line of thrust device or draft gear and the surfaces of revolution of main rotor end
It is parallel.
In order to simplify the structure of driving device, volume, the weight of driving device are reduced, manufacture easy to process is easy to repair
Maintenance is easy to use, and convenient for reducing cost, further preferred technical solution is that the thrust device or draft gear is drive
Dynamic motor is turbojet, and driving blade is housed on the output shaft of the driving motor.
For the ease of driving motor being driven to be rotated in a certain range around the end of main rotor by orienting fin, to overcome
The torque that gyroscopic effect generates main rotor aerofoil, while the connection of driving motor and main rotor end is also allowed for, it is further excellent
The technical solution of choosing is in addition, the driving motor installs the T-shaped tubulose knot of axle bed by installing axle bed and installation axle rotation connection
Structure is equipped with the bearing coordinated with installation axle, in T shape tubular structures in the cross through hole of the installation axle bed of T shape tubular structures
Installation axle bed vertical through holes in installation driving motor, the end of main rotor be equipped with spacer pin, in the peace of T shape tubular structures
The vertical outer surface for filling axle bed is equipped with and the corresponding limiting cotter way in spacer pin position.
In order to avoid the moment of inertia that is generated in main rotor rotary course caused by driving motor installation axle bending moment,
Further preferred technical solution is in addition, the center of gravity of the orientation fin, installation axle bed and driving motor is respectively positioned on installation axle
On axis.
The driving motor of driving force for the structure for simplifying driving motor or in order to further enhance to(for) main rotor, into one
Preferred technical solution is walked in addition, in one end of the driving motor equipped with driving flabellum, in the installation axle bed of T shape tubular structures
The vertical through holes other end be respectively provided with equipped with end cap or at the both ends of the driving motor driving flabellum or in T shape tubulose knots
Two output axis direction opposite driving motors are installed in the vertical through holes of the installation axle bed of structure.
Turning moment is generated to helicopter fuselage in order to balance main rotor, and also to convenient for controlling the yaw of helicopter
Course, further preferred technical solution in the tail portion of the vertically taking off and landing flyer in addition, be equipped with steering engine, steering engine and rudder
Connection.
For the ease of the electric energy on helicopter is transmitted on the drive motor on main rotor end, and can simultaneously by
Electric energy is transmitted on course driving steering engine, and preferred technical solution is in addition, the main rotor displacement system passes through bearing block and bearing
It is connect with hollow pipe, collector ring is set on the hollow pipe.
For the ease of the electric energy on helicopter is transmitted on the drive motor on main rotor end, and can simultaneously by
Electric energy be transmitted to course driving steering engine on, further preferred technical solution in addition, the driving motor by install axle bed with
And the conducting wire or conductive film being arranged on inside main rotor are electrically connected with collector ring.
It is effectively manipulated for the ease of the working condition to main rotor drive motor and course driving steering engine, and is it
Electric power is provided, further preferred technical solution is in addition, the collector ring is electrically connected by conducting wire with electron speed regulator, electronics tune
Fast device is electrically connected with master controller, and master controller is electrically connected with console, and master controller is also connected by power supervisor and power supply
It connects, also power supervisor is with being electrically connected for electron speed regulator, and course driving motor is also by steering engine and electron speed regulator and main control
Device is electrically connected, and master controller is also electrically connected with rudder row.
The advantages of the present invention are：The oil electric mixed dynamic active rotor vertically taking off and landing flyer has
It is simple in structure, can be greatly reduced to the driving power of main rotor or the quick driving force improved to main rotor, additionally it is possible to overcome top
Spiral shell effect is caused by main rotor the features such as torsional moment.As a result of oil electric mixed dynamic, the helicopter made is patrolled in low speed
Endurance can reach the effect of energy saving, and the driving force of main rotor can be increased substantially in high-performance cruise.
Description of the drawings
Fig. 1 is one of system structure diagram of oil electric mixed dynamic active rotor vertically taking off and landing flyer of the present invention；
Fig. 2 is the two of the system structure diagram of oil electric mixed dynamic active rotor vertically taking off and landing flyer of the present invention；
Fig. 3 is the front view of main rotor in oil electric mixed dynamic active rotor vertically taking off and landing flyer of the present invention；Fig. 3 .1 are
Partial enlarged view at the C of Fig. 3；
Fig. 4 be the A-A of Fig. 3 to diagram,
Fig. 5 is one of vertical view of Fig. 3；
Fig. 6 is the two of the vertical view of Fig. 3；
Fig. 7 is the three of the vertical view of Fig. 3
Fig. 8 .1 are the main structure diagrams of the installation axle bed in Fig. 3；
Fig. 8 .2 are the left view structural representations of the installation axle bed in Fig. 3；；
Fig. 8 .3 are the right side structural representations of the installation axle bed in Fig. 3；
Fig. 9 is the structure diagram that the installation axle bed in Fig. 3 is connect with orientation fin；
Figure 10 is the dimensional structure diagram of Fig. 9；
Figure 11 is the dimensional structure diagram of Fig. 3.
In figure：1st, main rotor；A1, preflow push rotor；2nd, main rotor displacement system；3rd, first clutch；4th, engine；
5th, second clutch；6th, generator；7th, power-supply controller of electric；8th, installation axle；9th, fin is oriented；10th, driving motor；11st, leaf is driven
Piece；The 12nd, axle bed is installed；13rd, bearing；14th, spacer pin；15th, cotter way is limited；16th, end cap；17th, steering engine；18th, bearing block；19th, axis
It holds；20th, hollow pipe；21st, collector ring；22nd, rudder；23rd, electron speed regulator；24th, master controller；25th, console；26th, power supply
Manager；27th, power supply.
Specific embodiment
With reference to the accompanying drawings and examples, the specific embodiment of the present invention is further described.Following embodiment is only
For clearly illustrating technical scheme of the present invention, and it is not intended to limit the protection scope of the present invention and limits the scope of the invention.
As shown in Figure 1, 2, the present invention is a kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer, the aircraft
Including at least two panels main rotor 1,1 one end of main rotor is connect with intermediate connector, and intermediate connector connects with main rotor displacement system 2
It connects, in thrust device or draft gear of the end of the every main rotor 1 equipped with driving main rotor rotation, main rotor displacement system
2 one end of uniting are connect by intermediate connector with main rotor 1, and the other end is connect with hollow pipe 20, before being equipped with below main rotor 1
To rotor A1 is promoted, the drive shaft of preflow push rotor A1 is connect by first clutch 3 with engine 4, and engine 4 also passes through
Second clutch 5 is connect with generator 6, and generator 6 is electrically connected with power-supply system 7.
Since rotor A1 one end of pushing ahead of the helicopter is connect with engine 4, it is also associated in the end of main rotor 1
Thrust device or draft gear.It therefore, can be by the connection between first clutch and 3 engines 4 when helicopter low cruise
It disconnects, only connect second clutch 5 with engine 4, engine 4 passes through the power generation arch thrust device of generator 6 or draft gear
Driving main rotor 1 rotates, while can also be accumulator electric power storage.When helicopter needs high-performance cruise, can by first clutch 3 with
Engine 4 connects, and the connection between second clutch 5 and engine 4 is disconnected, thrust device or draft gear can pass through at this time
The electric power of accumulator drives main rotor 1 by the end of main rotor 1, and engine 4 thus may be used by pushing ahead A1 rotor wing rotations
The driving force of main rotor 1 is greatly improved, the effect of Gauss cruise is reached.And in low cruise, due to thrust
Device or draft gear are installed in the end of main rotor 1, due to the effect of lever principle, in the case where output torque is identical
Driving force is also just smaller further away from the required thrust of rotation center, therefore thrust device or draft gear institute can be greatly reduced
Output power is needed, reaches the effect of energy saving.
As shown in Fig. 3~11, for the ease of the connection between thrust device or draft gear and main rotor end, protect simultaneously
1 reasonable stress of main rotor is demonstrate,proved, the preferred embodiment of the invention is that the thrust device or draft gear are by being arranged on main rotation
It is rotatablely connected between the installation axle 8 of 1 end of the wing and main rotor 1, and the axis of installation axle 8 is overlapped with the transverse axis of main rotor 1
Or it is parallel, the thrust direction of the thrust device or draft gear and the direction of rotation of main rotor 1 on the contrary, and with installation axle 8
Axis direction is vertical, is fixedly connected with orientation fin 9 in the side of the thrust device or draft gear, orientation fin 9 with it is every
The axis of thrust device or draft gear is symmetrical between 1 end of piece main rotor, orientation fin 9 is used to make thrust device or traction
The center line of device is parallel with the surfaces of revolution of 1 end of main rotor.
In order to simplify the structure of driving device, volume, the weight of driving device are reduced, manufacture easy to process is easy to repair
Maintenance is easy to use, and convenient for reducing cost, further preferred embodiment of the present invention is the thrust device or traction dress
It is set to driving motor 10 or for turbojet, driving blade 11 is housed on the output shaft of the driving motor 10.
As shown in Fig. 3~11, for the ease of driving driving motor 11 around the end of main rotor 1 one by orienting fin 9
Determine to rotate in range, with the torque that gyroscopic effect is overcome to generate 1 aerofoil of main rotor, while also allow for driving motor 10 and main rotation
The connection of 1 end of the wing, further preferred embodiment of the present invention in addition, the driving motor 10 by install axle bed 12 with peace
Dress axis 8 is rotatablely connected, and is installed 12 T-shaped tubular structure of axle bed, is pacified in the cross through hole of the installation axle bed 12 of T shape tubular structures
Equipped with the bearing 13 coordinated with installation axle 8, driving motor is installed in the vertical through holes of the installation axle bed 12 of T shape tubular structures
10, spacer pin 14 is equipped in the end of main rotor 1, is equipped with and limit in the vertical outer surface of the installation axle bed 12 of T shape tubular structures
The corresponding limiting cotter way 15 in position 14 position of pin.
As shown in Fig. 3~11, in order to avoid the moment of inertia generated in 1 rotary course of main rotor causes driving motor 10
8 bending moment of installation axle, further preferred embodiment of the present invention in addition, it is described orientation fin 9, installation axle bed 12 and drive
The center of gravity of dynamic motor 10 is respectively positioned on the axis of installation axle 8.
As shown in Fig. 3~11, for the structure that simplifies driving motor 10 or in order to further enhance driving motor 10 for
The driving force of main rotor 1, further preferred embodiment of the present invention is in addition, in one end of the driving motor 10 equipped with driving
Flabellum 11 is equipped with end cap 16 or in the driving motor 10 in the vertical through holes other end of the installation axle bed 12 of T shape tubular structures
Both ends be respectively provided with driving flabellum 11 or be equipped in the vertical through holes of the installation axle bed 12 of T shape tubular structures two it is defeated
Go out the opposite driving motor 10 of axis direction.
As shown in Fig. 3~11, turning moment is generated to helicopter fuselage in order to balance main rotor, and also to convenient for control
The yaw course of helicopter processed, further preferred embodiment of the present invention is in addition, in the tail portion of the vertically taking off and landing flyer
Equipped with steering engine 17, steering engine 17 is connect with rudder 22.
As shown in Fig. 3~11, for the ease of the electric energy on helicopter to be transmitted to the drive motor on 1 end of main rotor
On 10, and electric energy can be transmitted on course driving steering engine 17 simultaneously, the preferred embodiment of the invention is in addition, the main rotation
Wing displacement system 2 is connect by bearing block 18 and bearing 19 with hollow pipe 20, and collector ring 21 is set on the hollow pipe 20.
As shown in Fig. 3~11, for the ease of the electric energy on helicopter to be transmitted to the drive motor on 1 end of main rotor
On 10, and electric energy can be transmitted on course driving steering engine 17 simultaneously, further preferred embodiment of the present invention is in addition, institute
Driving motor 10 is stated to be electrically connected with collector ring 21 by the conducting wire or conductive film installed axle bed 12 and be arranged on inside main rotor 1
It connects.
As shown in Fig. 3~11, for the ease of the work shape to the driving motor 10 on main rotor 1 and course driving steering engine 17
State is effectively manipulated, and provides electric power for it, and further preferred embodiment of the present invention is in addition, the collector ring 21 is logical
It crosses conducting wire to be electrically connected with electron speed regulator 23,23 device of electronic speed regulation is electrically connected with master controller 24, master controller 24 and console
25 electrical connections, master controller 24 also connect by power supervisor 26 with power supply 27, also power supervisor 26 of electron speed regulator 23
With being electrically connected, course driving motor 17 is electrically connected also by steering engine 22 and electron speed regulator 23 with master controller 24, master controller
24 are also electrically connected with rudder row 22.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, several improvements and modifications can also be made, these improvements and modifications
Also it should be regarded as protection scope of the present invention.
Claims (10)
1. a kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer, which is characterized in that the aircraft includes at least two
Piece main rotor, main rotor one end are connect with intermediate connector, and intermediate connector is connect with main rotor displacement system, described in every
Thrust device or draft gear of the end of main rotor equipped with driving main rotor rotation, main rotor displacement system one end passes through centre
Connector is connect with main rotor, and the other end is connect with hollow pipe, and preflow push rotor, preflow push are equipped with below main rotor
The drive shaft of rotor is connect by first clutch with engine, and engine is also connect by second clutch with generator, hair
Motor is electrically connected with power-supply system.
2. oil electric mixed dynamic active rotor vertically taking off and landing flyer as described in claim 1, which is characterized in that the thrust
Device or draft gear are rotatablely connected, and the axis of installation axle by being arranged between the installation axle of main rotor end and main rotor
Transverse axis coincidence or parallel, the rotation side of the thrust direction and main rotor of the thrust device or draft gear with main rotor
To on the contrary, and it is vertical with the axis direction of installation axle, be fixedly connected with orientation in the side of the thrust device or draft gear
Fin, orients the axis that thrust device or draft gear are symmetrical between fin and every main rotor end, and orientation fin is used for
Make the center line of thrust device or draft gear parallel with the surfaces of revolution of main rotor end.
3. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 2, which is characterized in that the thrust
Device or draft gear are driving motor or are turbojet, equipped with driving leaf on the output shaft of the driving motor
Piece.
4. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 3, which is characterized in that the driving
Motor is rotatablely connected by installing axle bed with installation axle, the T-shaped tubular structure of axle bed is installed, in the installation axle of T shape tubular structures
The bearing coordinated with installation axle is installed in the cross through hole of seat, is pacified in the vertical through holes of the installation axle bed of T shape tubular structures
Fill driving motor, the end of main rotor be equipped with spacer pin, T shape tubular structures installation axle bed vertical outer surface be equipped with
The corresponding limiting cotter way in spacer pin position.
5. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 4, which is characterized in that the orientation
The center of gravity of fin, installation axle bed and driving motor is respectively positioned on the axis of installation axle.
6. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 5, which is characterized in that in the drive
One end of dynamic motor equipped with driving flabellum, T shape tubular structures installation axle bed the vertical through holes other end equipped with end cap or
The both ends of the driving motor are respectively provided with driving flabellum or are installed in the vertical through holes of the installation axle bed of T shape tubular structures
The driving motor for having two output axis directions opposite.
7. the oil electric mixed dynamic active rotor vertically taking off and landing flyer as described in claim 1 to 6 any one, feature exist
In in the tail portion of the vertically taking off and landing flyer equipped with steering engine, steering engine is connect with rudder.
8. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 7, which is characterized in that the main rotation
Wing displacement system is connect by bearing block and bearing with hollow pipe, and collector ring is set on the hollow pipe.
9. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 8, which is characterized in that the driving
Motor is electrically connected by installing axle bed and the conducting wire being arranged on inside main rotor or conductive film with collector ring.
10. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 9, which is characterized in that the collection
Electric ring is electrically connected by conducting wire with electron speed regulator, and electron speed regulator is electrically connected with master controller, master controller and console electricity
Connection, master controller are also connect by power supervisor with power supply, and electron speed regulator also with being electrically connected, drive power supervisor by course
Dynamic motor is electrically connected also by steering engine and electron speed regulator with master controller, and master controller is also electrically connected with rudder row.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810143121.XA CN108238247A (en) | 2018-02-11 | 2018-02-11 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
| PCT/CN2019/072640 WO2019154064A1 (en) | 2018-02-11 | 2019-01-22 | Gasoline-electric hybrid power vertical take-off and landing aircraft having driving rotors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810143121.XA CN108238247A (en) | 2018-02-11 | 2018-02-11 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108238247A true CN108238247A (en) | 2018-07-03 |
Family
ID=62698852
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810143121.XA Pending CN108238247A (en) | 2018-02-11 | 2018-02-11 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN108238247A (en) |
| WO (1) | WO2019154064A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110092000A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of all-electric tilting rotor wing unmanned aerial vehicle |
| CN110091999A (en) * | 2019-06-04 | 2019-08-06 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of method and structure flying the reduction rotary wings vertical take-off and landing drone main screw lift that electricity rises based on oil |
| WO2019154064A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Gasoline-electric hybrid power vertical take-off and landing aircraft having driving rotors |
| WO2019154067A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Active main rotor blade vertical take-off and landing aircraft |
| CN110450962A (en) * | 2019-08-20 | 2019-11-15 | 深圳市赛为智能股份有限公司 | Oil electric mixed dynamic unmanned plane and its working method |
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| CN2434225Y (en) * | 2000-06-30 | 2001-06-13 | 王志成 | Rotary wing helicopter |
| CN1335248A (en) * | 2000-07-20 | 2002-02-13 | 李小钢 | Helicopter with driving rotary wings |
| CN105836141A (en) * | 2016-04-12 | 2016-08-10 | 电子科技大学 | Driving mechanism and driving method of hybrid power helicopter |
| CN106564604A (en) * | 2016-04-13 | 2017-04-19 | 北京天宇新超航空科技有限公司 | Fuel-electric hybrid four-rotor power unit and control method thereof |
| CN208007286U (en) * | 2018-02-11 | 2018-10-26 | 桂艳春 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
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| CN110450962A (en) * | 2019-08-20 | 2019-11-15 | 深圳市赛为智能股份有限公司 | Oil electric mixed dynamic unmanned plane and its working method |
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