CN108163193B - A kind of active main rotor vertically taking off and landing flyer - Google Patents
A kind of active main rotor vertically taking off and landing flyer Download PDFInfo
- Publication number
- CN108163193B CN108163193B CN201810142091.0A CN201810142091A CN108163193B CN 108163193 B CN108163193 B CN 108163193B CN 201810142091 A CN201810142091 A CN 201810142091A CN 108163193 B CN108163193 B CN 108163193B
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- main rotor
- installation axle
- driving motor
- vertically taking
- traction device
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- 238000009434 installation Methods 0.000 claims abstract description 57
- 238000006073 displacement reaction Methods 0.000 claims abstract description 10
- 125000006850 spacer group Chemical group 0.000 claims description 8
- 241000883990 Flabellum Species 0.000 claims description 6
- 230000005484 gravity Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 8
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000004134 energy conservation Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 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
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect 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
- 230000005611 electricity Effects 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
- 230000035939 shock Effects 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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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
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of active main rotor vertically taking off and landing flyer, including 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 traction device of the end of every main rotor equipped with driving main rotor rotation, thrust device or traction device are rotatablely connected by being arranged between the installation axle and main rotor of main rotor end, and the axis of installation axle is axially coincident or parallel with the transverse direction of main rotor, the thrust direction of the thrust device or traction device is opposite with the direction of rotation of main rotor, orientation fin is fixedly connected in the side of thrust device or traction device, orientation fin is for keeping rotating shaft center's line of thrust device or traction device parallel with the surfaces of revolution of main rotor end.The aircraft has that structure is simple, can be greatly reduced to the driving power of main rotor or quickly improve the driving force 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 active main rotor VTOL flight
Device.
Background technique
It is well known that helicopter includes fuselage, is mounted on main rotor among fuselage on the top at position and for supporting
Disappear and is transferred to the anti torque tail rotor of the torque of fuselage from main rotor.
Hinged main rotor and/or antitorque rotor is also known.More specifically, hinged rotor includes around the
One axis rotation drive shaft, with drive shaft integrally surround first axle rotation propeller hub and from propeller hub along relative to
First axle is multiple blades that radial each second axis 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 relative to propeller hub around respective third axis, 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).
Occur such a demand in this field: in the case where not weakening the aerodynamic quality of rotor itself,
The vibration caused by a wide range of interior oscillating motion that weakens blade of the drive shaft around the rotation speed of first axle.
Currently, it is to provide power by built-in motor that machine helicopter, which generates power, 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 six monomers of output end one connection 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 the sky to flow downward
Air-flow generates upward lift to propeller 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, torque required for customer service air drag also can be very
Greatly.
Summary of the invention
It is an object of the invention to overcome defect existing in the prior art, provide that a kind of structure is simple, can be greatly reduced
Driving force or the quick driving force improved to main rotor to main rotor, additionally it is possible to overcome gyroscopic effect torsion caused by main rotor
The active main rotor vertically taking off and landing flyer of torque.
To achieve the above object, the technical scheme is to design a kind of active main rotor vertically taking off and landing flyer, institutes
Aircraft is stated including at least two panels main rotor, one end of main rotor is connect with intermediate connector, and intermediate connector and main rotor become
It is connected away from system, in thrust device or traction device of the end of every main rotor equipped with driving main rotor rotation, thrust device
Or traction device is rotatablely connected by being arranged between the installation axle and main rotor of main rotor end, and the axis of installation axle and master
The transverse direction of rotor is axially coincident or parallel, the thrust direction and the direction of rotation phase of main rotor of the thrust device or traction device
Instead, and it is vertical with the axis direction of installation axle, it is fixedly connected with orientation fin in the side of the thrust device or traction device,
The axis of thrust device or traction device is symmetrical between orientation fin and every main rotor end, orientation fin is for making thrust
Rotating shaft center's line of device or traction device is parallel with the surfaces of revolution of main rotor end.
Since main rotor one end of the helicopter is connect by main rotor displacement system with hollow pipe, in the end of main rotor
It is also connected with thrust device or traction device.Therefore when the end of Helicopter Main rotor is by thrust device or traction device driving master
Rotor wing rotation.Since thrust device or traction device are installed in the end of main rotor, due to the effect of lever principle, exporting
Moment of torsion driving force thrust required for rotation center in the case where is also just smaller, therefore thrust can be greatly reduced
Device or traction device output power reach effect of energy conservation.The setting of installation axle is for the ease of thrust device or traction dress
The connection between main rotor end is set, while guaranteeing main rotor reasonable stress,
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, preferred technical solution is that the thrust device or traction device are driving motor
Or be turbojet, driving blade is housed on the output shaft of the driving motor.
For the ease of driving driving motor to rotate in a certain range around the end of main rotor by orientation fin, to overcome
The torque that gyroscopic effect generates main rotor aerofoil, while it being also convenient for the connection of driving motor Yu main rotor end, preferred skill
Art scheme is in addition, the driving motor installs the T-shaped tubular structure of axle bed, in T shape pipe by installation axle bed and installation axis connection
Bearing with installation axle cooperation is installed, or by main rotor installation axle Position Design in the cross through hole of the installation axle bed of shape structure
For bearing block, installation axle is set by former T shape tubulose axle seating position, in the vertical through holes of the installation axle bed of T shape tubular structure
Interior installation driving motor is equipped with spacer pin in the end of main rotor, sets in the vertical outer surface of the installation axle bed of T shape tubular structure
There is limit cotter way corresponding with spacer pin position.
In order to avoid the moment of inertia installation axle bending moment caused by driving motor generated in main rotor rotary course,
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.
In order to simplify the structure of driving motor or the driving force in order to further enhance driving motor 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 structure
The vertical through holes other end be equipped with end cap.
In order to simplify the structure of driving motor or the driving force in order to further enhance driving motor for main rotor, into one
Preferred technical solution is walked in addition, being respectively provided with driving flabellum, or the peace in T shape tubular structure at the both ends of the driving motor
It fills in the vertical through holes of axle bed and two contrary driving motors of output shaft is installed, two driving motors can pass through positive and negative paddle
Keep power output direction identical.
Turning moment is generated in order to balance main rotor to helicopter fuselage, and also to convenient for the yaw of control helicopter
Course, further preferred technical solution is in addition, be equipped with course driving motor in the tail portion of the vertically taking off and landing flyer.
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 the driving motor of course, and preferred technical solution is in addition, main rotor displacement system passes through bearing block and bearing
It is connect with hollow pipe, is set with collector ring 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 is transmitted on the driving motor of course, further preferred technical solution in addition, the driving motor by installation axle bed with
And the conducting wire or conductive film being arranged in 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 motor, 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 also passes through power supervisor and power supply connects
Connect, electron speed regulator also power supervisor be electrically connected, course driving motor is also by steering engine and electron speed regulator and main control
Device electrical connection, master controller are also electrically connected with rudder row.
The advantages and beneficial effects of the present invention are: the active main rotor vertically taking off and landing flyer have structure it is simple,
The driving power or the quick driving force improved to main rotor to main rotor can be greatly reduced, additionally it is possible to overcome gyroscopic effect to master
Caused by rotor the features such as torsional moment.
Detailed description of the invention
Fig. 1 is the system structure diagram of active main rotor vertically taking off and landing flyer of the present invention；
Fig. 2 is the main view of main rotor in active main rotor vertically taking off and landing flyer of the present invention；
Fig. 2 .1 is partial enlargement diagram at the C of Fig. 2；
Fig. 3 is the A-A of Fig. 2 to diagram；
Fig. 4 is one of top view of Fig. 2；
Fig. 5 is the two of the top view of Fig. 2；
Fig. 6 is the three of the top view of Fig. 2
Fig. 7 .1 is the schematic view of the front view of the installation axle bed in Fig. 2；
Fig. 7 .2 is the left view structural representation of the installation axle bed in Fig. 2；；
Fig. 7 .3 is the right side structural representation of the installation axle bed in Fig. 2；
Fig. 8 is the structural schematic diagram that the installation axle bed in Fig. 2 is connect with orientation fin；
Fig. 9 is the schematic perspective view of Fig. 8；
Figure 10 is the schematic perspective view of Fig. 2.
In figure: 1, main rotor；2, main rotor displacement system；3, installation axle；4, fin is oriented；5, driving motor；6, it drives
Blade；7, axle bed is installed；8, bearing；9, spacer pin；10, cotter way is limited；11, end cap；12, course driving motor；13, bearing
Seat；14, bearing；15, hollow pipe；16, collector ring；17, steering engine；18, electron speed regulator；19, master controller；20, console；
21, power supervisor；22, power supply.
Specific embodiment
With reference to the accompanying drawings and examples, further description of the specific embodiments of the present invention.Following embodiment is only
For clearly illustrating technical solution of the present invention, and not intended to limit the protection scope of the present invention.
As shown in Fig. 1~10, the present invention is a kind of active main rotor vertically taking off and landing flyer, and the aircraft includes at least
One end of two panels main rotor 1, main rotor 1 is connect with intermediate connector, and intermediate connector is connect with main rotor displacement system 2,
The thrust device or traction device that the end of every main rotor 1 is rotated equipped with driving main rotor 1, thrust device or traction device are logical
It crosses between installation axle 3 and main rotor 1 that 1 end of main rotor is set and is rotatablely connected, and the axis of installation axle 3 and main rotor 1
It is laterally axially coincident or parallel, the thrust direction of the thrust device or traction device and the direction of rotation of main rotor 1 on the contrary, and
It is vertical with the axis direction of installation axle 1, it is fixedly connected with orientation fin 4 in the side of the thrust device or traction device, it is fixed
The axis of thrust device or traction device is symmetrical between airfoil 4 and every 1 end of main rotor, orientation fin 4 is for making to push away
Rotating shaft center's line of power device or traction device is parallel with the surfaces of revolution of main rotor end.
Since 1 one end of main rotor of the helicopter is connect by main rotor displacement system 2 with hollow pipe, in main rotor 1
End is also connected with thrust device or traction device.Therefore when the end of Helicopter Main rotor 1 is by thrust device or traction device
Main rotor 1 is driven to rotate.Since thrust device or traction device are installed in the end of main rotor 1, due to the work of lever principle
With driving force thrust required for rotation center is also just smaller in the identical situation of output torque, therefore can be big
Width reduces thrust device or traction device output power, reaches effect of energy conservation.The setting of installation axle 3 is for the ease of thrust dress
Set or 1 end of traction device and main rotor between connection, while guaranteeing 1 reasonable stress 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, the preferred embodiment of the invention is that the thrust device or traction device are to drive
Dynamic motor 5 is turbojet, and driving blade 6 is housed on the output shaft of the driving motor 5.
For the ease of driving driving motor 5 to rotate in a certain range around the end of main rotor 1 by orientation fin 4, with
The torque for overcoming gyroscopic effect to generate 1 aerofoil of main rotor, while it being also convenient for the connection of driving motor 5 Yu 1 end of main rotor, this
For invention preferred embodiment in addition, the driving motor 5 is connect by installing axle bed 7 with installation axle 3, installation axle bed 7 is T-shaped
Tubular structure is equipped with the bearing 8 cooperated with installation axle 3 in the cross through hole of the installation axle bed 7 of T shape tubular structure, or will
Main rotor installation axle Position Design is bearing block, installation axle is set by former T shape tubulose axle seating position, in T shape tubular structure
Installation axle bed 7 vertical through holes in install driving motor 5, the end of main rotor 1 be equipped with spacer pin 9, in T shape tubular structure
Installation axle bed 7 vertical outer surface be equipped with limit cotter way 10 corresponding with 9 position of spacer pin.
The moment of inertia generated during revolving 1 turn in order to avoid main rotor is to 3 bending force of installation axle caused by driving motor 5
Square, further preferred embodiment of the present invention is in addition, the center of gravity of the orientation fin 4, installation axle bed 7 and driving motor 5 is equal
On the axis of installation axle 3.
In order to simplify the structure of driving motor 5 or the driving force in order to further enhance driving motor 5 for main rotor 1,
Further preferred embodiment of the present invention is in addition, in one end of the driving motor 5 equipped with driving flabellum 6, in T shape tubulose knot
The vertical through holes other end of the installation axle bed 7 of structure is equipped with end cap 11.
In order to simplify the structure of driving motor 5 or the driving force in order to further enhance driving motor 5 for main rotor 1,
Further preferred embodiment of the present invention drives flabellum 6 in addition, being respectively provided at the both ends of the driving motor 5, or in T shape
Two contrary driving motors of output shaft 5, two driving electricity are installed in the vertical through holes of the installation axle bed 7 of tubular structure
Machine can keep power output direction identical by positive and negative paddle.
Turning moment is generated in order to balance main rotor 1 to helicopter fuselage, and also to convenient for the inclined of control helicopter
Boat course, further preferred embodiment of the present invention in the tail portion of the vertically taking off and landing flyer equipped with course in addition, drive
Motor 12.
For the ease of the electric energy on helicopter is transmitted on the drive motor 5 on 1 end of main rotor, and can be simultaneously
Electric energy is transmitted on course driving motor 12, the preferred embodiment of the invention is in addition, main rotor displacement system 2 passes through axis
It holds seat 13 and bearing 14 is connect with hollow pipe 15, be set with collector ring 16 on the hollow pipe 15.
For the ease of the electric energy on helicopter is transmitted on the drive motor 5 on 1 end of main rotor, and can be simultaneously
Electric energy is transmitted on course driving motor 12, further preferred embodiment of the present invention is in addition, the driving motor 5 passes through
Installation axle bed 7 and the conducting wire or conductive film being arranged in inside main rotor 1 are electrically connected with collector ring 16.
It is effectively manipulated for the ease of the working condition to main rotor drive motor 5 and course driving motor 12, and
Electric power is provided for it, further preferred embodiment of the present invention is in addition, the collector ring 16 passes through conducting wire and electron speed regulator
18 electrical connections, electron speed regulator 18 are electrically connected with master controller 19, and master controller 19 is electrically connected with console 20, master controller 19
Also connect with power supply 22 by power supervisor 21, electron speed regulator 18 also power supervisor 21 be electrically connected, course drives electric
Machine 12 is electrically connected also by steering engine 17 and electron speed regulator 18 with master controller 19, and master controller 19 is also electrically connected with rudder row 17.
The above is only a 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 active main rotor vertically taking off and landing flyer, which is characterized in that the aircraft includes at least two panels main rotor, main
Rotor one end is connect with intermediate connector, and intermediate connector is connect with main rotor displacement system, is filled in the end of every main rotor
There are the thrust device or traction device of driving main rotor rotation, thrust device or traction device are by being arranged in main rotor end
It is rotatablely connected between installation axle and main rotor, and the axis of installation axle is axially coincident or parallel with the transverse direction of main rotor, it is described to push away
The thrust direction of power device or traction device with the direction of rotation of main rotor on the contrary, and it is vertical with the axis direction of installation axle,
The side of the thrust device or traction device is fixedly connected with orientation fin, and it is right between fin and every main rotor end to orient
Claim the axis in thrust device or traction device, orientation fin for make rotating shaft center's line of thrust device or traction device with
The surfaces of revolution of main rotor end is parallel.
2. active main rotor vertically taking off and landing flyer as described in claim 1, which is characterized in that the thrust device or traction
Device is driving motor or is turbojet, and driving blade is housed on the output shaft of the driving motor.
3. active main rotor vertically taking off and landing flyer as claimed in claim 2, which is characterized in that the driving motor passes through peace
Axle bed and installation axis connection are filled, the T-shaped tubular structure of axle bed is installed, in the cross through hole of the installation axle bed of T shape tubular structure
Be equipped with installation axle cooperation bearing, or by main rotor installation axle Position Design be bearing block, by former T shape tubulose bearing seat
It installs and is set to installation axle, driving motor is installed in the vertical through holes of the installation axle bed of T shape tubular structure, in the end of main rotor
Equipped with spacer pin, spacer pin corresponding with spacer pin position is equipped in the vertical outer surface of the installation axle bed of T shape tubular structure
Slot.
4. active main rotor vertically taking off and landing flyer as claimed in claim 3, which is characterized in that the orientation fin, installation
The center of gravity of axle bed and driving motor is respectively positioned on the axis of installation axle.
5. active main rotor vertically taking off and landing flyer as claimed in claim 4, which is characterized in that the one of the driving motor
End is equipped with end cap equipped with driving flabellum, in the vertical through holes other end of the installation axle bed of T shape tubular structure.
6. active main rotor vertically taking off and landing flyer as claimed in claim 3, which is characterized in that the two of the driving motor
End is respectively provided with driving flabellum, or two output axis directions are equipped in the vertical through holes of the installation axle bed of T shape tubular structure
Opposite driving motor.
7. the active main rotor vertically taking off and landing flyer as described in claim 1 to 6 any one, which is characterized in that described
The tail portion of vertically taking off and landing flyer is equipped with course driving motor.
8. active main rotor vertically taking off and landing flyer as claimed in claim 7, which is characterized in that main rotor displacement system is logical
It crosses bearing block and bearing is connect with hollow pipe, be set with collector ring on the hollow pipe.
9. active main rotor vertically taking off and landing flyer as claimed in claim 8, which is characterized in that the driving motor passes through peace
Dress axle bed and the conducting wire or conductive film being arranged in inside main rotor are electrically connected with collector ring.
10. active main rotor vertically taking off and landing flyer as claimed in claim 9, which is characterized in that the collector ring is by leading
Line is electrically connected with electron speed regulator, and electron speed regulator is electrically connected with master controller, and master controller is electrically connected with console, main control
Device is also connected to power supply by power supervisor, electron speed regulator also power supervisor be electrically connected, course driving motor also leads to
It crosses steering engine and electron speed regulator is electrically connected with master controller, master controller is also electrically connected with rudder row.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810142091.0A CN108163193B (en) | 2018-02-11 | 2018-02-11 | A kind of active main rotor vertically taking off and landing flyer |
| PCT/CN2019/072657 WO2019154067A1 (en) | 2018-02-11 | 2019-01-22 | Active main rotor blade vertical take-off and landing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810142091.0A CN108163193B (en) | 2018-02-11 | 2018-02-11 | A kind of active main rotor vertically taking off and landing flyer |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108163193A CN108163193A (en) | 2018-06-15 |
| CN108163193B true CN108163193B (en) | 2019-09-20 |
Family
ID=62514191
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810142091.0A Active CN108163193B (en) | 2018-02-11 | 2018-02-11 | A kind of active main rotor vertically taking off and landing flyer |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN108163193B (en) |
| WO (1) | WO2019154067A1 (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163193B (en) * | 2018-02-11 | 2019-09-20 | 桂艳春 | A kind of active main rotor vertically taking off and landing flyer |
| CN108238247A (en) * | 2018-02-11 | 2018-07-03 | 桂艳春 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
| IT201900006604A1 (en) * | 2019-05-07 | 2020-11-07 | Vinati S R L | ROTATING WING AIRCRAFT EQUIPPED WITH IMPROVED PROPULSIVE SYSTEM |
| FR3113893B1 (en) * | 2020-09-04 | 2022-10-21 | Philippe Crochat | Yaw stabilized stator rotary wing aircraft |
| FR3113892B1 (en) * | 2020-09-04 | 2022-09-02 | Philippe Crochat | Rotary wing aircraft with blade tip motorization and variable pitch |
| CN114252262B (en) * | 2021-12-09 | 2023-12-08 | 中国船舶重工集团公司第七0三研究所 | Helicopter main reducer hub load simulation loading device considering balanced static dead weight |
| CN114476043A (en) * | 2021-12-31 | 2022-05-13 | 中国航天空气动力技术研究院 | Electronic distributing type rotor unmanned transport plane |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2434226Y (en) * | 2000-07-20 | 2001-06-13 | 李小钢 | Active rotary wing helicopter |
| CN1335248A (en) * | 2000-07-20 | 2002-02-13 | 李小钢 | Helicopter with driving rotary wings |
| CN2502994Y (en) * | 2001-05-27 | 2002-07-31 | 尚晓 | Rotor with power |
| WO2015089679A1 (en) * | 2013-12-20 | 2015-06-25 | Conca-Garcia Raphaël | Vertical takeoff and landing aircraft (vtol) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163193B (en) * | 2018-02-11 | 2019-09-20 | 桂艳春 | A kind of active main rotor vertically taking off and landing flyer |
| CN108238247A (en) * | 2018-02-11 | 2018-07-03 | 桂艳春 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
| 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 |
| CN207956057U (en) * | 2018-02-11 | 2018-10-12 | 桂艳春 | A kind of active main rotor vertically taking off and landing flyer |
-
2018
- 2018-02-11 CN CN201810142091.0A patent/CN108163193B/en active Active
-
2019
- 2019-01-22 WO PCT/CN2019/072657 patent/WO2019154067A1/en active Application Filing
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2434226Y (en) * | 2000-07-20 | 2001-06-13 | 李小钢 | Active rotary wing helicopter |
| CN1335248A (en) * | 2000-07-20 | 2002-02-13 | 李小钢 | Helicopter with driving rotary wings |
| CN2502994Y (en) * | 2001-05-27 | 2002-07-31 | 尚晓 | Rotor with power |
| WO2015089679A1 (en) * | 2013-12-20 | 2015-06-25 | Conca-Garcia Raphaël | Vertical takeoff and landing aircraft (vtol) |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108163193A (en) | 2018-06-15 |
| WO2019154067A1 (en) | 2019-08-15 |
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