CN207956057U - 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
- CN207956057U CN207956057U CN201820246350.XU CN201820246350U CN207956057U CN 207956057 U CN207956057 U CN 207956057U CN 201820246350 U CN201820246350 U CN 201820246350U CN 207956057 U CN207956057 U CN 207956057U
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- CN
- China
- Prior art keywords
- main rotor
- driving motor
- installation axle
- draft gear
- vertically taking
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
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Abstract
The utility model 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 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 draft gear is opposite with the direction of rotation of main rotor, it is fixedly connected with orientation fin in the side of thrust device or draft gear, orientation fin is for keeping 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 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 utility model is related to vertically taking off and landing flyer for technical field, and in particular to a kind of active main rotor VTOL
Aircraft.
Background technology
It is well known that helicopter includes fuselage, the main rotor among the fuselage on the top at position 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 includes around the
One axis rotation drive shaft, with drive shaft integrally surround first axle rotation propeller hub and from propeller hub upper edge 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 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 where not weakening the aerodynamic quality of rotor itself,
It is vibrated caused by a wide range of interior oscillating motion that weakens blade of the drive shaft around the rotary 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 output end one connection, six monomers of upright parallel shaft, makes the propeller blade of six monomers horizontally rotate
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.
Utility model content
The purpose of the utility model is to overcome defect existing in the prior art, provide it is a kind of it is simple in structure, can be substantially
It reduces the driving force to main rotor or quickly improves the driving force to main rotor, additionally it is possible to gyroscopic effect be overcome to cause main rotor
Torsional moment active main rotor vertically taking off and landing flyer.
To achieve the above object, the technical solution of the utility model is a kind of active main rotor VTOL flight of design
Device, the aircraft include at least two panels main rotor, and one end of main rotor is connect with intermediate connector, intermediate connector and main rotation
Wing displacement system connects, 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 and main rotor of main rotor end, and the axis of installation axle
It is axially coincident or parallel with the transverse direction of main rotor, the rotation side of the thrust direction and main rotor of the thrust device or draft gear
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
Keep rotating shaft center's line of thrust device or draft gear 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 energy saving effect.The setting of installation axle is for the ease of thrust device or traction dress
The connection between main rotor end is set, while ensureing 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 driving motor 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 coordinated 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, it sets former T shapes tubulose axle seating position to 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
There is limit cotter way corresponding with 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.
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 structures
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 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
Keep power output direction identical.
Turning moment is generated to helicopter fuselage in order to balance main rotor, and also to convenient for the yaw of control 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, 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 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
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 is electrically connected, and master controller is also electrically connected with rudder row.
The advantages of the utility model and advantageous effect are：The active main rotor vertically taking off and landing flyer has structure letter
List can be greatly reduced the driving power to 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 of the drawings
Fig. 1 is the system structure diagram of the utility model active main rotor vertically taking off and landing flyer；
Fig. 2 is the front view of main rotor in the utility model active main rotor vertically taking off and landing flyer；
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 structural schematic 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：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 implementation mode
With reference to the accompanying drawings and examples, specific embodiment of the present utility model is further described.Implement below
Example is only used for clearly illustrating the technical solution of the utility model, and the protection model of the utility model cannot be limited with this
It encloses.
As shown in Fig. 1~10, the utility model is a kind of active main rotor vertically taking off and landing flyer, and the aircraft is at least
Including two panels main rotor 1, one end of main rotor 1 is connect with intermediate connector, and intermediate connector connects with main rotor displacement system 2
It connects, in 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 traction
Device is rotatablely connected by being arranged between the installation axle 3 and main rotor 1 of 1 end of main rotor, and the axis of installation axle 3 and main rotation
The transverse direction of the wing 1 is axially coincident or parallel, the thrust direction of the thrust device or draft gear and the direction of rotation phase of main rotor 1
Instead, and it is vertical with the axis direction of installation axle 1, it is fixedly connected with orientation fin in the side of the thrust device or draft gear
4, the axis that thrust device or draft gear are symmetrical between fin 4 and every 1 end of main rotor is oriented, orientation fin 4 is used for
Keep rotating shaft center's line of thrust device or draft gear 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
Main rotor 1 is driven to rotate.Since thrust device or draft gear are installed in the end of main rotor 1, due to the work of lever principle
With, it is also just smaller further away from the required thrust of rotation center in the identical driving force of output torque, therefore can be big
Width reduces thrust device or draft gear output power, reaches energy saving effect.The setting of installation axle 3 is filled for the ease of thrust
Set or 1 end of draft gear and main rotor between connection, while ensureing 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 utility model preferred embodiment is the thrust device or draft gear
For driving motor 5 or it is turbojet, driving blade 6 is housed on the output shaft of the driving motor 5.
For the ease of driving driving motor 5 to be rotated in a certain range around the end of main rotor 1 by orienting fin 4, with
The torque for overcoming gyroscopic effect 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
Utility model preferred embodiment in addition, the driving motor 5 by install axle bed 7 connect with installation axle 3, installation axle bed 7
T-shaped tubular structure is equipped with the bearing 8 coordinated with installation axle 3 in the cross through hole of the installation axle bed 7 of T shape tubular structures,
Or by main rotor installation axle Position Design be bearing block, former T shapes tubulose axle seating position is set to installation axle, in T shape tubuloses
Driving motor 5 is installed in the vertical through holes of the installation axle bed 7 of structure, spacer pin 9 is equipped in the end of main rotor 1, in T shape tubuloses
The vertical outer surface of the installation axle bed 7 of structure is equipped with limit cotter way corresponding with 9 position of spacer pin 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, the utility model further preferred embodiment is in addition, the weight for orienting fin 4, installing axle bed 7 and driving motor 5
The heart is respectively positioned 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,
The utility model further preferred embodiment is in addition, in one end of the driving motor 5 equipped with driving flabellum 6, in T shape pipes
The vertical through holes other end of the installation axle bed 7 of shape 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,
The utility model further preferred embodiment drives flabellum 6 in addition, being respectively provided at the both ends of the driving motor 5, or
Two opposite driving motors 5 of output axis direction are installed in the vertical through holes of the installation axle bed 7 of T shape tubular structures, two
Driving motor can keep 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, the utility model further preferred embodiment in the tail portion of the vertically taking off and landing flyer in addition, be equipped with course
Driving 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 same
When electric energy is transmitted on course driving motor 12, the utility model preferred embodiment is in addition, main rotor displacement system 2
It is connect with hollow pipe 15 by bearing block 13 and bearing 14, 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 same
When electric energy is transmitted on course driving motor 12, the utility model further preferred embodiment is in addition, the driving is electric
Machine 5 is electrically connected by the conducting wire or conductive film installed axle bed 7 and be arranged inside main rotor 1 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, the utility model further preferred embodiment is in addition, the collector ring 16 passes through conducting wire and electronics tune
Fast device 18 is electrically connected, and electron speed regulator 18 is electrically connected with master controller 19, and master controller 19 is electrically connected with console 20, master control
Device 19 processed is also connect by power supervisor 21 with power supply 22, electron speed regulator 18 also power supervisor 21 be electrically connected, navigate
Be electrically connected to driving motor 12 with master controller 19 also by steering engine 17 and electron speed regulator 18, master controller 19 also with rudder row
17 electrical connections.
The above is only the preferred embodiment of the utility model, it is noted that for the common skill of the art
For art personnel, without deviating from the technical principle of the utility model, several improvements and modifications can also be made, these change
The scope of protection of the utility model is also should be regarded as into retouching.
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 draft gear of driving main rotor rotation, thrust device or draft gear 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 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 coordinated with installation axle is installed, or by main rotor installation axle Position Design is bearing block, 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, spacer pin corresponding with spacer pin position is equipped 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 are 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 main rotor displacement system is logical
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 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, 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 (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820246350.XU CN207956057U (en) | 2018-02-11 | 2018-02-11 | A kind of active main rotor vertically taking off and landing flyer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820246350.XU CN207956057U (en) | 2018-02-11 | 2018-02-11 | A kind of active main rotor vertically taking off and landing flyer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207956057U true CN207956057U (en) | 2018-10-12 |
Family
ID=63738892
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820246350.XU Withdrawn - After Issue CN207956057U (en) | 2018-02-11 | 2018-02-11 | A kind of active main rotor vertically taking off and landing flyer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207956057U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163193A (en) * | 2018-02-11 | 2018-06-15 | 桂艳春 | A kind of active main rotor vertically taking off and landing flyer |
| WO2019154064A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Gasoline-electric hybrid power vertical take-off and landing aircraft having driving rotors |
| IT201900006604A1 (en) * | 2019-05-07 | 2020-11-07 | Vinati S R L | ROTATING WING AIRCRAFT EQUIPPED WITH IMPROVED PROPULSIVE SYSTEM |
| RU2799627C2 (en) * | 2019-05-07 | 2023-07-07 | Винати С.Р.Л. | Rotor wing aircraft with improved propulsion system |
-
2018
- 2018-02-11 CN CN201820246350.XU patent/CN207956057U/en not_active Withdrawn - After Issue
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163193A (en) * | 2018-02-11 | 2018-06-15 | 桂艳春 | A kind of active main rotor vertically taking off and landing flyer |
| 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 |
| IT201900006604A1 (en) * | 2019-05-07 | 2020-11-07 | Vinati S R L | ROTATING WING AIRCRAFT EQUIPPED WITH IMPROVED PROPULSIVE SYSTEM |
| WO2020224871A1 (en) * | 2019-05-07 | 2020-11-12 | Vinati S.R.L. | Rotary wing aircraft with improved propulsion system |
| RU2799627C2 (en) * | 2019-05-07 | 2023-07-07 | Винати С.Р.Л. | Rotor wing aircraft with improved propulsion system |
| US11858619B2 (en) | 2019-05-07 | 2024-01-02 | Vinati S.R.L. | Rotary wing aircraft with improved propulsion system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20181012 Effective date of abandoning: 20190920 |