CN108163193A - 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
- CN108163193A CN108163193A CN201810142091.0A CN201810142091A CN108163193A CN 108163193 A CN108163193 A CN 108163193A CN 201810142091 A CN201810142091 A CN 201810142091A CN 108163193 A CN108163193 A CN 108163193A
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- Prior art keywords
- main rotor
- installation axle
- driving motor
- draft gear
- vertically taking
- Prior art date
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- 238000009434 installation Methods 0.000 claims abstract description 56
- 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 6
- 230000009471 action Effects 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 230000005611 electricity Effects 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
- 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
- 230000003313 weakening effect Effects 0.000 description 2
- 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
- 230000035939 shock 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
-
- 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 draft gear of the end of every main rotor equipped with driving main rotor rotation, thrust device or draft gear are rotatablely connected by being arranged between the installation axle of main rotor end and main rotor, 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 draft gear is opposite with the direction of rotation of main rotor, orientation fin is fixedly connected in the side of thrust device or draft gear, orientation fin is used to make rotating shaft center's line of thrust device or draft gear parallel with the surfaces of revolution of main rotor end.The aircraft 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 active main rotor VTOL flight
Device.
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
The active main rotor vertically taking off and landing flyer of torque.
To achieve the above object, the technical scheme is that designing a kind of active main rotor vertically taking off and landing flyer, institute
Aircraft is stated including at least two panels main rotor, one end of main rotor is connect with intermediate connector, and intermediate connector becomes with main rotor
It is connected away from system, in thrust device or draft gear of the end of every main rotor equipped with driving main rotor rotation, thrust device
Or draft gear is rotatablely connected by being arranged between the installation axle of main rotor end and main rotor, and the axis of installation axle and master
The transverse direction of rotor is axially coincident or parallel, the thrust direction of the thrust device or draft gear and the direction of rotation phase of main rotor
Instead, it is and vertical with the axis direction of installation axle, orientation fin is fixedly connected in the side of the thrust device or draft gear,
The axis of thrust device or draft gear is symmetrical between orientation fin and every main rotor end, orientation fin is used to make thrust
Rotating shaft center's line of device or draft gear 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 associated with thrust device or draft gear.Therefore when the end of Helicopter Main rotor is by thrust device or draft gear driving master
Rotor wing rotation.Since thrust device or draft gear are installed in the end of main rotor, due to the effect of lever principle, exporting
Moment of torsion driving force in the case of is also just smaller further away from the required thrust of rotation center, therefore thrust can be greatly reduced
Device or draft gear output power, reach the effect of energy saving.The setting of installation axle is for the ease of thrust device or traction dress
The connection between main rotor end is put, while ensures 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 draft gear are driving motor
Or be turbojet, 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, preferred skill
Art scheme is in addition, the driving motor installs the T-shaped tubular structure of axle bed, in T shape pipes by installing axle bed and installation axis connection
The bearing that coordinates with installation axle 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, former T shapes tubulose axle seating position is set as installation axle, in the vertical through holes of the installation axle bed of T shape tubular structures
Interior installation driving motor is equipped with spacer pin in the end of main rotor, is set in the vertical outer surface of the installation axle bed of T shape tubular structures
Have 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 equipped with end cap.
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, being respectively provided with driving flabellum or the peace in T shape tubular structures at the both ends of the driving motor
It fills and two output axis direction opposite driving motors is installed in the vertical through holes of axle bed, two driving motors can pass through positive and negative paddle
Make power output direction identical.
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 course driving motor.
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, 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 is transmitted on the driving motor of course, 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 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 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 active main rotor vertically taking off and landing flyer have it is simple in structure,
The driving power to main rotor or the quick driving force improved 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.
Description of the drawings
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 front view of main rotor in active main rotor vertically taking off and landing flyer of the present invention；
Fig. 2 .1 are close-up schematic views at the C of Fig. 2；
Fig. 3 is the A-A of Fig. 2 to diagram；
Fig. 4 is one of vertical view of Fig. 2；
Fig. 5 is the two of the vertical view of Fig. 2；
Fig. 6 is the three of the vertical view of Fig. 2
Fig. 7 .1 are the main structure diagrams of the installation axle bed in Fig. 2；
Fig. 7 .2 are the left view structural representations of the installation axle bed in Fig. 2；；
Fig. 7 .3 are the right side structural representations of the installation axle bed in Fig. 2；
Fig. 8 is the structure diagram that the installation axle bed in Fig. 2 is connect with orientation fin；
Fig. 9 is the dimensional structure diagram of Fig. 8；
Figure 10 is the dimensional structure diagram of Fig. 2.
In figure：1st, main rotor；2nd, main rotor displacement system；3rd, installation axle；4th, fin is oriented；5th, driving motor；6th, it drives
Blade；The 7th, axle bed is installed；8th, bearing；9th, spacer pin；10th, cotter way is limited；11st, end cap；12nd, course driving motor；13rd, bearing
Seat；14th, bearing；15th, hollow pipe；16th, collector ring；17th, steering engine；18th, electron speed regulator；19th, master controller；20th, console；
21st, power supervisor；22nd, 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 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
Two panels main rotor 1, one end of main rotor 1 are connect with intermediate connector, and intermediate connector is connect with main rotor displacement system 2,
The thrust device or draft gear that the end of every main rotor 1 is rotated equipped with driving main rotor 1, thrust device or draft gear lead to
It crosses to be arranged between the installation axle 3 of 1 end of main rotor and main rotor 1 and be 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 draft gear and the direction of rotation of main rotor 1 on the contrary, and
It is vertical with the axis direction of installation axle 1, orientation fin 4 is fixedly connected in the side of the thrust device or draft gear, it is fixed
The axis of thrust device or draft gear is symmetrical between airfoil 4 and every 1 end of main rotor, orientation fin 4 is used to make to push away
Rotating shaft center's line of power apparatus or draft gear 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 associated with thrust device or draft gear.Therefore when the end of Helicopter Main rotor 1 is by thrust device or draft gear
Driving main rotor 1 rotates.Since thrust device or draft gear are installed in the end of main rotor 1, due to the work of lever principle
With in the case where output torque is identical, driving force is also just smaller further away from the required thrust of rotation center, therefore can be big
Width reduces thrust device or draft gear output power, reaches the effect of energy saving.The setting of installation axle 3 is filled for the ease of thrust
Put or 1 end of draft gear and main rotor between connection, while ensure 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 draft gear is 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 motor 5 being driven to be rotated in a certain range around the end of main rotor 1 by orienting fin 4, with
The torque that gyroscopic effect is overcome to generate 1 aerofoil of main rotor, while the connection of driving motor 5 and 1 end of main rotor is also allowed for, 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 coordinated with installation axle 3 or is incited somebody to action in the cross through hole of the installation axle bed 7 of T shape tubular structures
Main rotor installation axle Position Design is bearing block, former T shapes tubulose axle seating position is set as installation axle, in T shape tubular structures
Installation axle bed 7 vertical through holes in installation driving motor 5, the end of main rotor 1 be equipped with spacer pin 9, in T shape tubular structures
Installation axle bed 7 vertical outer surface be equipped with and 9 position of spacer pin it is corresponding limiting cotter way 10.
In order to avoid main rotor revolves the moment of inertia generated during 1 turn 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.
The driving motor 5 of driving force for the structure for simplifying driving motor 5 or in order to further enhance to(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 knots
The vertical through holes other end of the installation axle bed 7 of structure is equipped with end cap 11.
The driving motor 5 of driving force for the structure for simplifying driving motor 5 or in order to further enhance to(for) main rotor 1,
Further preferred embodiment of the present invention is in addition, be respectively provided with driving flabellum 6 at the both ends of the driving motor 5 or in T shapes
Two opposite driving motors 5 of output axis direction, two driving electricity are installed in the vertical through holes of the installation axle bed 7 of tubular structure
Machine can make power output direction identical by positive and negative paddle.
Turning moment is generated to helicopter fuselage in order to balance main rotor 1, 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, the main rotor displacement system 2 passes through axis
Bearing 13 and bearing 14 are connect with hollow pipe 15, and collector ring 16 is set 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 that are arranged on 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
It is also connect by power supervisor 21 with power supply 22, also power supervisor 21 is with being electrically connected for electron speed regulator 18, course driving electricity
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 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 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, in the end dress of every main rotor
There are the thrust device or draft gear of driving main rotor rotation, thrust device or draft gear are by being arranged on 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 apparatus or draft gear 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 draft gear 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 draft gear, orientation fin for make rotating shaft center's line of thrust device or draft gear 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 structures
The bearing that coordinates with installation axle is installed or it is bearing block by main rotor installation axle Position Design, by former T shapes 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 structures, in the end of main rotor
Equipped with spacer pin, it is equipped with and the corresponding spacer pin in spacer pin position in the vertical outer surface of the installation axle bed of T shape tubular structures
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 structures.
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 is equipped in the vertical through holes of the installation axle bed of T shape tubular structures
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 the main rotor displacement system leads to
It crosses bearing block and bearing is connect with hollow pipe, collector ring is set 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 that are arranged on 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 connect by power supervisor with power supply, and also with being electrically connected, course driving motor also leads to power supervisor electron speed regulator
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 true CN108163193A (en) | 2018-06-15 |
| CN108163193B 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) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019154067A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Active main rotor blade vertical take-off and landing aircraft |
| WO2019154064A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Gasoline-electric hybrid power vertical take-off and landing aircraft having driving rotors |
| CN113015676A (en) * | 2019-05-07 | 2021-06-22 | 维纳缇有限公司 | Rotorcraft with improved propulsion system |
| 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 |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| 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 |
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- 2019-01-22 WO PCT/CN2019/072657 patent/WO2019154067A1/en active Application Filing
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| 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) |
| CN207956057U (en) * | 2018-02-11 | 2018-10-12 | 桂艳春 | A kind of active main rotor vertically taking off and landing flyer |
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| WO2019154067A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Active main rotor blade vertical take-off and landing aircraft |
| WO2019154064A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Gasoline-electric hybrid power vertical take-off and landing aircraft having driving rotors |
| CN113015676A (en) * | 2019-05-07 | 2021-06-22 | 维纳缇有限公司 | Rotorcraft with improved propulsion system |
| 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 |
| CN114476043B (en) * | 2021-12-31 | 2024-08-09 | 中国航天空气动力技术研究院 | Unmanned conveyer of electronic distributing type rotor |
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| WO2019154067A1 (en) | 2019-08-15 |
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