CN208007286U - A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer - Google Patents
A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer Download PDFInfo
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- CN208007286U CN208007286U CN201820246670.5U CN201820246670U CN208007286U CN 208007286 U CN208007286 U CN 208007286U CN 201820246670 U CN201820246670 U CN 201820246670U CN 208007286 U CN208007286 U CN 208007286U
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Abstract
The utility model discloses a kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer, the aircraft includes at least two panels main rotor, main rotor one end is connect with intermediate connector, intermediate connector is connect with main rotor displacement system, in thrust device or draft gear of the end of the every main rotor equipped with driving main rotor rotation, main rotor displacement system one end is connect by intermediate connector with main rotor, the other end is connect with hollow pipe, preflow push rotor is equipped with below main rotor, the drive shaft of preflow push rotor is connect by first clutch with engine, engine is also connect by second clutch with generator, generator is electrically connected with power-supply controller of electric.The oil electric mixed dynamic active rotor vertically taking off and landing flyer have it is simple in structure, can be greatly reduced to the driving power of main rotor or 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 oil electric mixed dynamic actively rotation
Wing vertically taking off and landing flyer.
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 a kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer.
To achieve the above object, the technical solution of the utility model is that a kind of oil electric mixed dynamic active rotor of design is vertical
Landing aircraft, the aircraft include at least two panels main rotor, and main rotor one end is connect with intermediate connector, intermediate connector
It is connect with main rotor displacement system, in the end of the every main rotor equipped with the thrust device or traction for driving main rotor rotation
Device, main rotor displacement system one end are connect by intermediate connector with main rotor, and the other end is connect with hollow pipe, in main rotor
Below be equipped with preflow push rotor, the drive shaft of preflow push rotor connect by first clutch with engine, engine
It is also connect with generator by second clutch, generator is electrically connected with power-supply system.
Since preflow push rotor one end of the helicopter is connect with engine, thrust is also associated in the end of main rotor
Device or draft gear.Therefore when helicopter low cruise, the connection between first clutch and engine can be disconnected, only
Second clutch is connect with engine, engine drives main rotor to revolve by electrical power generators arch thrust device or draft gear
Turn, while can also be accumulator electric power storage.When helicopter needs high-performance cruise, first clutch can be connect with engine, it will
Connection between second clutch and engine disconnects, and thrust device or draft gear can be by the electric power of accumulator by leading at this time
The end of rotor drives main rotor, engine to be rotated by preflow push preflow push rotor A1, thus can be significantly
The driving force for improving preflow push rotor A1, reaches the effect of high-performance cruise.And in low cruise, due to thrust device
Or draft gear is installed in the end of main rotor, due to the effect of lever principle, drives in the case that output torque is identical
Power is also just smaller further away from the required thrust of rotation center, therefore can be greatly reduced defeated needed for thrust device or draft gear
Go out power, reaches energy saving effect.
For the ease of the connection between thrust device or draft gear and main rotor end, while ensureing that main rotor stress is closed
Reason, preferred technical solution are that the thrust device or draft gear are by being arranged installation axle and main rotation in main rotor end
It is rotatablely connected between the wing, and the axis of installation axle is overlapped with the transverse axis of main rotor or parallel, the thrust device or traction
The thrust direction of device with the direction of rotation of main rotor on the contrary, and it is vertical with the axis direction of installation axle, in the thrust device
Or the side of draft gear is fixedly connected with orientation fin, orients and is symmetrical with thrust device between fin and every main rotor end
Or the axis of draft gear, orientation fin are used to make the surfaces of revolution of the center line of thrust device or draft gear and main rotor end
It is parallel.
In order to simplify the structure of driving device, volume, the weight of driving device are reduced, manufacture easy to process is easy to repair
Maintenance is easy to use, and convenient for reducing cost, further preferred technical solution is that the thrust device or draft gear are to drive
Dynamic motor is turbojet, and 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, it is further excellent
The technical solution of choosing is in addition, the driving motor installs the T-shaped tubulose knot of axle bed by installing axle bed and installation axle rotation connection
Structure is equipped with the bearing coordinated with installation axle, in T shape tubular structures in the cross through hole of the installation axle bed of T shape tubular structures
Installation axle bed vertical through holes in install driving motor, the end of main rotor be equipped with spacer pin, in the peace of T shape tubular structures
The vertical outer surface for filling axle bed is equipped with 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 end cap is housed, or be respectively provided with driving flabellum at the both ends of the driving motor, or in T shape tubulose knots
Two output axis direction opposite driving motors are installed in the vertical through holes of the installation axle bed of structure.
Turning moment is generated to helicopter fuselage in order to balance main rotor, and also to convenient for 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 steering engine, steering engine and rudder
Connection.
For the ease of the electric energy on helicopter is transmitted on the drive motor on main rotor end, and can simultaneously by
Electric energy is transmitted on course driving steering engine, and preferred technical solution is in addition, main rotor displacement system passes through bearing block and bearing
It is connect with hollow pipe, collector ring is set on the hollow pipe.
For the ease of the electric energy on helicopter is transmitted on the drive motor on main rotor end, and can simultaneously by
Electric energy be transmitted to course driving steering engine on, further preferred technical solution in addition, the driving motor by install axle bed with
And the conducting wire or conductive film being arranged inside main rotor are electrically connected with collector ring.
For the ease of driving the working condition of steering engine effectively to be manipulated in main rotor drive motor and course, and it 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 oil electric mixed dynamic active rotor vertically taking off and landing flyer
With 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 gram
Gyroscopic effect is taken caused by main rotor the features such as torsional moment.As a result of oil electric mixed dynamic, the helicopter made is low
Energy saving effect can be reached when speed cruise, the driving force of main rotor can be increased substantially in high-performance cruise.
Description of the drawings
Fig. 1 be the utility model oil electric mixed dynamic active rotor vertically taking off and landing flyer system structure diagram it
One；
Fig. 2 be the utility model oil electric mixed dynamic active rotor vertically taking off and landing flyer system structure diagram it
Two；
Fig. 3 is the front view of main rotor in the utility model oil electric mixed dynamic active rotor vertically taking off and landing flyer；
Fig. 4 is the A-A of Fig. 3 to diagram, and Fig. 4 .1 are partial enlarged views at the C of Fig. 4；
Fig. 5 is one of vertical view of Fig. 3；
Fig. 6 is the two of the vertical view of Fig. 3；
Fig. 7 is the three of the vertical view of Fig. 3；
Fig. 8 .1 are the main structure diagrams of the installation axle bed in Fig. 3；
Fig. 8 .2 are the left view structural representations of the installation axle bed in Fig. 3；
Fig. 8 .3 are the right side structural representations of the installation axle bed in Fig. 3；
Fig. 9 is the structural schematic diagram that the installation axle bed in Fig. 3 is connect with orientation fin；
Figure 10 is the dimensional structure diagram of Fig. 9；
Figure 11 is the dimensional structure diagram of Fig. 3.
In figure：1, main rotor；A1, preflow push rotor；2, main rotor displacement system；3, first clutch；4, engine；
5, second clutch；6, generator；7, power-supply controller of electric；8, installation axle；9, fin is oriented；10, driving motor；11, leaf is driven
Piece；12, axle bed is installed；13, bearing；14, spacer pin；15, cotter way is limited；16, end cap；17, steering engine；18, bearing block；19, axis
It holds；20, hollow pipe；21, collector ring；22, rudder；23, electron speed regulator；24, master controller；25, console；26, power supply
Manager；27, 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 Figure 1, 2, the utility model is a kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer, described to fly
Row device includes at least two panels main rotor 1, and 1 one end of main rotor is connect with intermediate connector, intermediate connector and main rotor displacement system
2 connection of system, in thrust device or draft gear of the end of the every main rotor 1 equipped with driving main rotor rotation, main rotor
2 one end of displacement system is connect by intermediate connector with main rotor 1, and the other end is connect with hollow pipe 20, below main rotor 1
Equipped with preflow push rotor A1, the drive shaft of preflow push rotor A1 is connect by first clutch 3 with engine 4, engine 4
It is also connect with generator 6 by second clutch 5, generator 6 is electrically connected with power-supply system 7.
Since one end rotor A1 of pushing ahead of the helicopter is connect with engine 4, it is also connected in the end of main rotor 1
There are thrust device or draft gear.It therefore, can be by the company between first clutch and 3 engines 4 when helicopter low cruise
Disconnection is connect, only connect second clutch 5 with engine 4, engine 4 is filled by the power generation arch thrust device of generator 6 or traction
It sets driving main rotor 1 to rotate, while can also be accumulator electric power storage.It, can be by first clutch 3 when helicopter needs high-performance cruise
It connect, the connection between second clutch 5 and engine 4 is disconnected, thrust device or draft gear can lead at this time with engine 4
The electric power for crossing accumulator drives main rotor 1 by the end of main rotor 1, and engine 4 is by pushing ahead A1 rotor wing rotations, thus
The driving force of main rotor 1 can be greatly improved, reach the effect of Gauss cruise.And in low cruise, due to pushing away
Power apparatus or draft gear are installed in the end of main rotor 1, due to the effect of lever principle, in the identical situation of output torque
Lower driving force is also just smaller further away from the required thrust of rotation center, therefore thrust device or draft gear can be greatly reduced
Required output power reaches energy saving effect.
As shown in Fig. 3~11, for the ease of the connection between thrust device or draft gear and main rotor end, protect simultaneously
1 reasonable stress of main rotor is demonstrate,proved, the utility model preferred embodiment is that the thrust device or draft gear are existed by setting
It is rotatablely connected between the installation axle 8 and main rotor 1 of 1 end of main rotor, and the transverse axis of the axis of installation axle 8 and main rotor 1
It overlaps or parallel, the thrust direction of the thrust device or draft gear is with the direction of rotation of main rotor 1 on the contrary, and and installation axle
8 axis direction is vertical, the side of the thrust device or draft gear be fixedly connected with orientation fin 9, orientation fin 9 with
The axis of thrust device or draft gear is symmetrical between every 1 end of main rotor, orientation fin 9 is for making thrust device or leading
The center line of leading-in device is parallel with the surfaces of revolution of 1 end of main rotor.
In order to simplify the structure of driving device, volume, the weight of driving device are reduced, manufacture easy to process is easy to repair
Maintenance is easy to use, and convenient for reducing cost, the utility model further preferred embodiment is, the thrust device or is led
Leading-in device is driving motor 10 or is turbojet, and driving blade is housed on the output shaft of the driving motor 10
11。
As shown in Fig. 3~11, for the ease of driving driving motor 11 around the end of main rotor 1 one by orienting fin 9
Determine rotation in range, with the torque for overcoming gyroscopic effect to generate 1 aerofoil of main rotor, while also allowing for driving motor 10 and main rotation
The connection of 1 end of the wing, the utility model further preferred embodiment is in addition, the driving motor 10 passes through installation axle bed 12
It is rotatablely connected with installation axle 8,12 T-shaped tubular structure of axle bed is installed, it is logical in the transverse direction of the installation axle bed 12 of T shape tubular structures
The bearing 13 coordinated with installation axle 8 is installed in hole, driving is installed in the vertical through holes of the installation axle bed 12 of T shape tubular structures
Motor 10 is equipped with spacer pin 14 in the end of main rotor 1, is equipped in the vertical outer surface of the installation axle bed 12 of T shape tubular structures
Limit cotter way corresponding with 14 position of spacer pin 15.
As shown in Fig. 3~11, in order to avoid the moment of inertia generated in 1 rotary course of main rotor causes driving motor 10
8 bending moment of installation axle, the utility model further preferred embodiment in addition, the orientation fin 9, installation axle bed 12
It is respectively positioned on the center of gravity of driving motor 10 on the axis of installation axle 8.
As shown in Fig. 3~11, in order to simplify driving motor 10 structure or in order to further enhance driving motor 10 for
The driving force of main rotor 1, the utility model further preferred embodiment in one end of the driving motor 10 in addition, be equipped with
Flabellum 11 is driven, end cap 16 is housed in the vertical through holes other end of the installation axle bed 12 of T shape tubular structures, or in driving electricity
The both ends of machine 10 are respectively provided with driving flabellum 11, or are equipped with two in the vertical through holes of the installation axle bed 12 of T shape tubular structures
Platform exports the opposite driving motor 10 of axis direction.
As shown in Fig. 3~11, turning moment is generated to helicopter fuselage in order to balance main rotor, and also to convenient for control
The yaw course of helicopter processed, the utility model further preferred embodiment is in addition, in the vertically taking off and landing flyer
Tail portion is equipped with steering engine 17, and steering engine 17 is connect with rudder 22.
As shown in Fig. 3~11, for the ease of the electric energy on helicopter to be transmitted to the drive motor on 1 end of main rotor
On 10, and electric energy can be transmitted on course driving steering engine 17 simultaneously, the utility model preferred embodiment is in addition, described
Main rotor displacement system 2 is connect by bearing block 18 and bearing 19 with hollow pipe 20, and collector ring is set on the hollow pipe 20
21。
As shown in Fig. 3~11, for the ease of the electric energy on helicopter to be transmitted to the drive motor on 1 end of main rotor
On 10, and electric energy can be transmitted on course driving steering engine 17 simultaneously, the utility model further preferred embodiment is also
Have, the driving motor 10 is by installing axle bed 12 and the conducting wire or conductive film that are arranged inside main rotor 1 and collector ring 21
Electrical connection.
As shown in Fig. 3~11, for the ease of the work shape to driving motor 10 and course driving steering engine 17 on main rotor 1
State is effectively manipulated, and provides electric power for it, and the utility model further preferred embodiment is in addition, the collector ring
21 are electrically connected by conducting wire with electron speed regulator 23, and 23 device of electronic speed regulation is electrically connected with master controller 24, master controller 24 and control
Platform 25 processed is electrically connected, and master controller 24 is also connect by power supervisor 26 with power supply 27, the also power supply pipe of electron speed regulator 23
It manages device 26 and is electrically connected, course driving motor 17 is electrically connected also by steering engine 22 and electron speed regulator 23 with master controller 24, main
Controller 24 is also electrically connected with rudder row 22.
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 oil electric mixed dynamic active rotor vertically taking off and landing flyer, which is characterized in that the aircraft includes at least two
Piece main rotor, main rotor one end are connect with intermediate connector, and intermediate connector is connect with main rotor displacement system, described in every
Thrust device or draft gear of the end of main rotor equipped with driving main rotor rotation, main rotor displacement system one end passes through centre
Connector is connect with main rotor, and the other end is connect with hollow pipe, and preflow push rotor, preflow push are equipped with below main rotor
The drive shaft of rotor is connect by first clutch with engine, and engine is also connect by second clutch with generator, hair
Motor is electrically connected with power-supply system.
2. oil electric mixed dynamic active rotor vertically taking off and landing flyer as described in claim 1, which is characterized in that the thrust
Device or draft gear are rotatablely connected by being arranged between the installation axle and main rotor of main rotor end, and the axis of installation axle
With the coincidence of the transverse axis of main rotor or parallel, 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 the center line of thrust device or draft gear parallel with the surfaces of revolution of main rotor end.
3. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 2, which is characterized in that the thrust
Device or draft gear are driving motor or are turbojet, equipped with driving leaf on the output shaft of the driving motor
Piece.
4. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 3, which is characterized in that the driving
Motor is rotatablely connected by installing axle bed with installation axle, the T-shaped tubular structure of axle bed is installed, in the installation axle of T shape tubular structures
The bearing coordinated with installation axle is installed in the cross through hole of seat, is pacified in the vertical through holes of the installation axle bed of T shape tubular structures
Fill driving motor, the end of main rotor be equipped with spacer pin, T shape tubular structures installation axle bed vertical outer surface be equipped with
The corresponding limit cotter way in spacer pin position.
5. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 4, which is characterized in that the orientation
The center of gravity of fin, installation axle bed and driving motor is respectively positioned on the axis of installation axle.
6. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 5, which is characterized in that in the drive
One end of dynamic motor 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, or
The both ends of the driving motor are respectively provided with driving flabellum, or are installed in the vertical through holes of the installation axle bed of T shape tubular structures
The driving motor for having two output axis directions opposite.
7. the oil electric mixed dynamic active rotor vertically taking off and landing flyer as described in claim 1 to 6 any one, feature exist
In in the tail portion of the vertically taking off and landing flyer equipped with steering engine, steering engine is connect with rudder.
8. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 7, which is characterized in that the main rotation
Wing displacement system is connect by bearing block and bearing with hollow pipe, and collector ring is set on the hollow pipe.
9. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 6, which is characterized in that the driving
Motor is electrically connected by the conducting wire or conductive film installed axle bed and be arranged inside main rotor with collector ring.
10. oil electric mixed dynamic active rotor vertically taking off and landing flyer as claimed in claim 9, which is characterized in that the collection
Electric ring is electrically connected by conducting wire with electron speed regulator, and electron speed regulator is electrically connected with master controller, master controller and console electricity
Connection, master controller also connect by power supervisor with power supply, electron speed regulator also power supervisor be electrically connected, course drive
Dynamic motor is electrically connected also by steering engine and electron speed regulator with master controller, and master controller is also electrically connected with rudder row.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820246670.5U CN208007286U (en) | 2018-02-11 | 2018-02-11 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820246670.5U CN208007286U (en) | 2018-02-11 | 2018-02-11 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208007286U true CN208007286U (en) | 2018-10-26 |
Family
ID=63886516
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820246670.5U Active CN208007286U (en) | 2018-02-11 | 2018-02-11 | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208007286U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| WO2019154067A1 (en) * | 2018-02-11 | 2019-08-15 | 桂艳春 | Active main rotor blade vertical take-off and landing aircraft |
-
2018
- 2018-02-11 CN CN201820246670.5U patent/CN208007286U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
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