CN208248494U - A kind of rotor system of titling coaxial bispin wing aircraft - Google Patents
A kind of rotor system of titling coaxial bispin wing aircraft Download PDFInfo
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- CN208248494U CN208248494U CN201820427193.2U CN201820427193U CN208248494U CN 208248494 U CN208248494 U CN 208248494U CN 201820427193 U CN201820427193 U CN 201820427193U CN 208248494 U CN208248494 U CN 208248494U
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- rotor
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- shaft
- propeller hub
- bevel gear
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Abstract
The utility model discloses a kind of rotor systems of titling coaxial bispin wing aircraft, comprising: upper rotor driver, including upper rotor, upper propeller hub, upper rotor shaft and upper pitch, the rotation inner ring of the upper pitch and upper rotor are hinged by upper pitch-change-link；Lower rotor driver, and upper rotor driver mirror symmetry, the upper pitch does not rotate outer ring and do not rotate outer ring with lower pitch to be connected by the way that three isometric control sticks are parallel；So that up and down the period of rotor away from always away from synchronous with controlled；Transmission device: including left and right transmission shaft, gear drive group, upper and lower rotor shaft and left and right transmission shaft are passed through the ratcheting connection of four bevel gears by the gear drive group.The utility model is by using upper and lower coaxial separate type bispin wing structure, power is transmitted between two rotors, this structure is in addition to overcoming aircraft rotation, also rotor system is set to vert using the torsion of two engines, neutral and revolution, to make rotor system that there is good comprehensive stability performance.
Description
Technical field
The utility model relates to a kind of space flight and aviation technical fields, especially tilting coaxial rotor aircraft.
Background technique
It is well known that fixed wing aircraft is unable to VTOL, helicopter cannot fly high as propeller fixed wing aircraft,
It is swift-winged, flies far, is fuel-efficient；And helicopter can not need runway, landing maneuverability with VTOL.Tilting type rotor
Machine had not only had VTOL as pure helicopter and hovering ability, but also had the cruising flight as fixed wing aircraft
Speed is big, voyage farther out the features such as.Tiltrotor is considered aeronautical chart development prospect by the researcher of various countries at present and answers
With one of highest aircraft of value.
Tiltrotor not only has VTOL and high-performance cruise performance, and mobility is very strong, so application field
And its it is wide.20th century mid-term, the U.S. started the research to tilting rotor technology, which starts from XV-3, and maturation is in XV-
25, it is applied to V-22 osprey.Its advantage does not have to describe in detail, but has many disadvantages yet, for example, tilt rotor aircraft (such as V-22) due to
Existing rotor has wing again, and to realize that rotor verts from upright position to horizontal position or horizontal position to upright position,
Therefore be respectively disposed on two wing outer ends rotor mechanism and engine nacelle rotor wing rotation or during vert it is pneumatic and pass
Sense environment is different, and two feathers are also asynchronous, will make aircraft uneven extremely as long as there is such as collar vortex；And by
It is huge in rotor and nacelle inertia, it is difficult to control, therefore easily cause the accident.
Utility model content
Technical problem to be solved by the utility model is: it is winged to provide a kind of titling coaxial DCB Specimen that work is more stable
The rotor system of machine.
The solution that the utility model solves its technical problem is: a kind of rotor system of titling coaxial bispin wing aircraft
System, including upper rotor driver comprising upper rotor, upper propeller hub, upper rotor shaft and upper pitch, the upper propeller hub are fixed on rotation
The upper end of wing axis, the upper rotor connect with upper propeller hub axis, and the upper pitch is located at the lower section of upper propeller hub, and the upper rotor shaft is worn
The upper pitch is crossed, the upper pitch is connect with upper rotor by upper pitch-change-link, the both ends of the upper pitch-change-link
It is hinged with upper pitch, upper rotor respectively；Lower rotor driver comprising lower rotor, lower propeller hub, lower rotor shaft and lower pitch,
The lower propeller hub is fixed on the lower end of lower rotor shaft, and the lower rotor connects with lower propeller hub axis, and the lower pitch is located at lower propeller hub
Top, the lower rotor shaft passes through the lower pitch, and the lower pitch connect with lower rotor by lower pitch-change-link,
The both ends of the lower pitch-change-link are hinged with lower pitch, lower rotor respectively；The upper rotor shaft is overlapped with lower rotor shaft axle center,
And the lower end of upper rotor shaft and the upper end of lower rotor shaft leave each other, and the steering and the steering phase of lower rotorshaft of upper rotor shaft
Instead；The motionless outer ring of the upper pitch is parallel hinged by three one control levers with the motionless outer ring of lower pitch；Transmission device,
Including left drive shaft, right transmission shaft, gear drive, the left drive shaft is overlapped with the axle center of right transmission shaft, left drive shaft
The left end of right end and right transmission shaft leave each other；The gear drive by upper rotor shaft, lower rotor shaft and left drive shaft,
Right transmission shaft connects.
As the further improvement of following technical proposals, the gear drive includes upper bevel gear, lower bevel gear, a left side
Bevel gear and right bevel gear, the upper bevel gear covers admittedly with upper rotor shaft to be connect, and the lower bevel gear and lower rotor shaft cover company admittedly
It connecing, the left angular wheel covers admittedly with left drive shaft to be connect, and the right bevel gear covers admittedly with right transmission shaft to be connect, and left angular wheel/
The upper and lower ends of right bevel gear are ratcheting with upper bevel gear, lower bevel gear respectively, steering and the right transmission shaft of the left drive shaft
It turns to opposite.
As the further improvement of following technical proposals, the upper rotor includes rotor folder and rotor, and the rotor is solid
It is scheduled on the outer end of rotor folder, the inner end of the rotor folder is equipped with shaft, and the upper propeller hub includes rotor axis hole, the shaft
It covers in rotor axis hole, the upper pitch-change-link and rotor folder are hinged.
As the further improvement of following technical proposals, by upper between the rotation inner ring and upper propeller hub of the upper pitch
Transmission arm connection；It is connected between the rotation inner ring of the lower pitch and lower propeller hub by underdrive arm.
It further include steering engine as the further improvement of following technical proposals, the steering engine is connect with joystick driver.
As the further improvement of following technical proposals, the steering engine has three, and the control stick also has three, three behaviour
Vertical pole it is parallel to each other and respectively with the rocker arm hinge on the motionless outer ring of upper and lower pitch.
The beneficial effects of the utility model are: the utility model changes the structure of the mature coaxial aircraft of tradition, use
The bispin wing structure of upper and lower coaxial separate type, for power from positive and negative transmitting is carried out between two rotors, this structure is winged except overcoming
Outside machine rotation, rotor system can also be made to vert using the torsion of two engines, neutral and revolution, so that rotor system be made to have
There is good comprehensive stability performance.
Detailed description of the invention
It, below will be to required in embodiment description in order to illustrate more clearly of the technical scheme in the embodiment of the utility model
Attached drawing to be used is briefly described.Obviously, described attached drawing is a part of the embodiment of the utility model, rather than complete
Portion's embodiment, those skilled in the art without creative efforts, can also be obtained according to these attached drawings it
His design scheme and attached drawing.
Fig. 1 is the stereoscopic schematic diagram of the utility model.
Specific embodiment
It is carried out below with reference to technical effect of the embodiment and attached drawing to the design of the utility model, specific structure and generation
It clearly and completely describes, to be completely understood by the purpose of this utility model, feature and effect.Obviously, described embodiment
It is a part of the embodiment of the utility model, rather than whole embodiments, it is based on the embodiments of the present invention, the skill of this field
Art personnel other embodiments obtained without creative efforts belong to the model of the utility model protection
It encloses.In addition, all connection/connection relationships being previously mentioned in text, not singly refer to that component directly connects, and referring to can be according to specific reality
Situation is applied, by adding or reducing couple auxiliary, to form more preferably coupling structure.Each technology in the invention is special
Sign, can be with combination of interactions under the premise of not conflicting conflict.
Referring to Fig.1, a kind of rotor system of titling coaxial bispin wing aircraft, including upper rotor driver 1 comprising upper rotation
The wing 11, upper propeller hub 12, upper rotor shaft 13 and upper pitch 14, the upper propeller hub 12 is fixed on the upper end of rotor shaft 13, described
Upper rotor 11 connects with upper 12 axis of propeller hub, and the upper pitch 14 is located at the lower section of upper propeller hub 12, and the upper rotor shaft 13 passes through institute
The upper pitch 14 stated, the upper pitch 14 are connect with upper rotor 11 by upper pitch-change-link 15, the upper pitch-change-link 15
Both ends it is hinged with upper pitch 14, upper rotor 11 respectively；Lower rotor driver 2 comprising lower rotor 21, lower propeller hub 22, backspin
Wing axis 23 and lower pitch 24, the lower propeller hub 22 are fixed on the lower end of lower rotor shaft 23, the lower rotor 21 and lower propeller hub 22
Axis connects, and the lower pitch 24 is located at the top of lower propeller hub 22, and the installation direction of upper pitch and lower pitch is on the contrary, described
Lower rotor shaft 23 passes through the lower pitch 24, and the lower pitch 24 is connect with lower rotor 21 by lower pitch-change-link 25,
The both ends of the lower pitch-change-link 25 are hinged with the motionless outer ring of the motionless outer ring of lower pitch 24, lower rotor 21 respectively；It is described
Upper rotor shaft 13 is overlapped with lower 23 axle center of rotor shaft, and the lower end of upper rotor shaft 13 and the upper end of lower rotor shaft 23 leave each other,
And the steering of upper rotor shaft 13 is opposite with the steering of lower rotorshaft 23；The upper pitch 14 passes through two with lower pitch 24
Above control stick 4 connects, the upper and lower ends of control stick 4 respectively with the motionless outer ring of upper pitch 14, lower pitch 24 not
Dynamic outer ring is hinged, by realizing the synchronously control of tilted upward disk using operating stick, allows rotor and lower rotor same
Walk with width realize feathering and always away from variation；Transmission device 3, including left drive shaft 31, right transmission shaft 32, gear drive
Mechanism 33, the left drive shaft 31 are overlapped with the axle center of right transmission shaft 32, a left side for the right end of left drive shaft 31 and right transmission shaft 32
End leaves each other；The gear drive 33 connects upper rotor shaft 13, lower rotor shaft 23 and left drive shaft 31, right transmission shaft 32
It picks up and.
Preferred upper and lower rotor has three pieces blade, and upper three pieces blade is dextrorotation, and lower three pieces blade is derotation, Er Qieshang
Rotor is identical with the size of lower rotor, contrary due to upper and lower rotor, so that the operation reaction of three axis of aircraft is quick, and
The anti-twisted power of upper and lower rotor is cancelled out each other, and stability is more preferable.
It is further used as preferred embodiment, the gear drive 33 includes upper bevel gear, lower bevel gear, left cone
Gear and right bevel gear, the upper bevel gear are fixedly connected with upper rotor shaft 13, and the lower bevel gear and lower rotor shaft 23 are fixed
Connection, the left angular wheel is fixedly connected with left drive shaft 31, so right bevel gear is fixedly connected with right transmission shaft 32, and left cone
Gear/right bevel gear upper and lower ends are ratcheting with upper bevel gear, lower bevel gear respectively, the steering of the left drive shaft and right transmission
The steering of axis is opposite.By utilizing bevel gear, the deflecting of transmission can be easily realized.
It is further used as preferred embodiment, the upper rotation 11 includes rotor folder 111 and rotor 112, the rotor
112 are fixed on the outer end of rotor folder 111, and the inner end of the rotor folder 111 is equipped with shaft, and the upper propeller hub 12 includes rotor
Axis hole, the shaft is solidly set in rotor axis hole and upper rotary wing oar jig 111 and upper propeller hub 12 is rigidly connected by shaft, described
Upper pitch-change-link 15 and rotor folder 111 are hinged；The connection method of lower 21 corresponding component of rotor is same as above.Rotor is fixedly mounted at
In rotor folder, and rotor folder and propeller hub are attached by shaft, so that rotor connect no flapping hinge, shimmy with propeller hub
Hinge, only pitch hinge avoid rotor and transmission device up and down and interfere during verting, and aircraft is being flown
When more safety and stability.
It is further used as preferred embodiment, by upper between the rotation inner ring and upper propeller hub 12 of the upper pitch 14
Transmission arm 16 connects；It is connected between the rotation inner ring of the lower pitch 24 and lower propeller hub 22 by underdrive arm 26.Using this
Structure can make the rotation inner ring of tilted upward disk and upper and lower rotor shaft rotate synchronously.
It is further used as preferred embodiment, further includes steering engine, the steering engine and control stick 4 are drivingly connected.The rudder
Machine have three be used to control always away from and the period away from variation, the control stick 4 has three and an equal length, three one control levers 4 at
120 degree parallel hinged with the rocker arm on the motionless outer ring of upper pitch 14 and lower pitch 24 respectively, and tilted upward disk uses
It is all 120 ° of pitches more general in existing helicopter.Control stick described in three is flat with the axle center of upper and lower rotor shaft
Row, and phase angle is 120 ° to three isometric control sticks between any two, is controlled by synchronizing same amplitude using CCPM mixing mode
The period screw pitch of upper and lower rotor and always away from realizing the lifting of aircraft and the variation in course.
The better embodiment of the utility model is illustrated below, but the invention be not limited to it is described
Embodiment, those skilled in the art can also make various equivalent changes without departing from the spirit of the present invention
Type or replacement, these equivalent variation or replacement are all included in the scope defined by the claims of the present application.
Claims (6)
1. a kind of rotor system of titling coaxial bispin wing aircraft, it is characterised in that: include:
Upper rotor driver (1) comprising upper rotor (11), upper propeller hub (12), upper rotor shaft (13) and upper pitch (14), it is described
Upper propeller hub (12) is fixed on the upper end of rotor shaft (13), and the upper rotor (11) connects with upper propeller hub (12) axis, the upper inclination
Disk (14) is located at the lower section of upper propeller hub (12), and the upper rotor shaft (13) passes through the upper pitch (14), the upper inclination
Disk (14) is connect with upper rotor (11) by upper pitch-change-link (15), the both ends of the upper pitch-change-link (15) respectively with upper inclination
Disk (14), upper rotor (11) are hinged；
Lower rotor driver (2) comprising lower rotor (21), lower propeller hub (22), lower rotor shaft (23) and lower pitch (24) are described
Lower propeller hub (22) is fixed on the lower end of lower rotor shaft (23), and the lower rotor (21) connects with lower propeller hub (22) axis, the lower inclination
Disk (24) is located at the top of lower propeller hub (22), and the lower rotor shaft (23) passes through the lower pitch (24), the lower inclination
Disk (24) is connect with lower rotor (21) by lower pitch-change-link (25), the both ends of the lower pitch-change-link (25) respectively with lower inclination
Disk (24), lower rotor (21) are hinged；
The upper rotor shaft (13) is overlapped with lower rotor shaft (23) axle center, and the lower end of upper rotor shaft (13) and lower rotor shaft (23)
Upper end leave each other, and the steering of upper rotor shaft (13) is opposite with the steering of lower rotor shaft (23)；The upper pitch (14)
Connect with lower pitch (24) by three isometric control sticks (4), the upper and lower ends of control stick (4) respectively with upper pitch
(14), lower pitch (24) is parallel hinged；
Transmission device (3), including left drive shaft (31), right transmission shaft (32), gear drive (33), the left drive shaft
(31) it is overlapped with the axle center of right transmission shaft (32), the left end of the right end and right transmission shaft (32) of left drive shaft (31) leaves each other；
The gear drive (33) connects upper rotor shaft (13), lower rotor shaft (23) and left drive shaft (31), right transmission shaft (32)
It picks up and.
2. the rotor system of titling coaxial bispin wing aircraft according to claim 1, it is characterised in that: the gear passes
Motivation structure (33) includes upper bevel gear, lower bevel gear, left angular wheel and right bevel gear, the upper bevel gear and upper rotor shaft (13)
Gu set connects admittedly for set connection, the lower bevel gear and lower rotor shaft (23), the left angular wheel and left drive shaft (31) Gu Taolian
Connect, set connects admittedly for the right bevel gear and right transmission shaft (32), and left angular wheel/right bevel gear upper and lower ends respectively with epicone
Gear, lower bevel gear are ratcheting, and the steering of the left drive shaft is opposite with the steering of right transmission shaft.
3. the rotor system of titling coaxial bispin wing aircraft according to claim 2, it is characterised in that: the upper rotor
It (11) include rotor folder (111) and rotor (112), the rotor (112) is fixed on the outer end of rotor folder (111), described
The inner end that rotor presss from both sides (111) is equipped with bearing and shaft, and the upper propeller hub (12) includes rotor axis hole, and the shaft is solidly set on rotation
Get up in wing axis hole and by upper propeller hub (12) and upper rotary wing oar jig (111) rigid connection, the upper pitch-change-link (15) and rotor
It is hinged that paddle presss from both sides (111).
4. the rotor system of titling coaxial bispin wing aircraft according to claim 1, it is characterised in that: the upper inclination
It is connect between the rotation inner ring of disk (14) and upper propeller hub (12) by upper transmission arm (16)；In the rotation of the lower pitch (24)
It is connect between ring and lower propeller hub (22) by underdrive arm (26).
5. the rotor system of titling coaxial bispin wing aircraft according to claim 1, it is characterised in that: further include rudder
Machine, the steering engine and control stick (4) are drivingly connected.
6. the rotor system of titling coaxial bispin wing aircraft according to claim 5, it is characterised in that: the steering engine has
Three, the upper pitch (14) and lower pitch (24) include rocker arm, and the rocker arm installs pitch (14)/have a down dip
On the motionless outer ring of swash plate (24), three one control levers (4) are isometric and hinged with rocker arm parallel to each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820427193.2U CN208248494U (en) | 2018-03-27 | 2018-03-27 | A kind of rotor system of titling coaxial bispin wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820427193.2U CN208248494U (en) | 2018-03-27 | 2018-03-27 | A kind of rotor system of titling coaxial bispin wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208248494U true CN208248494U (en) | 2018-12-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820427193.2U Expired - Fee Related CN208248494U (en) | 2018-03-27 | 2018-03-27 | A kind of rotor system of titling coaxial bispin wing aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN208248494U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108298072A (en) * | 2018-03-27 | 2018-07-20 | 佛山科学技术学院 | A kind of rotor system of titling coaxial bispin wing aircraft |
| CN110979653A (en) * | 2019-12-28 | 2020-04-10 | 苏州韬讯航空科技有限公司 | Three-steering-engine coaxial dual-rotor system and control strategy thereof |
-
2018
- 2018-03-27 CN CN201820427193.2U patent/CN208248494U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108298072A (en) * | 2018-03-27 | 2018-07-20 | 佛山科学技术学院 | A kind of rotor system of titling coaxial bispin wing aircraft |
| CN108298072B (en) * | 2018-03-27 | 2023-09-26 | 佛山科学技术学院 | Rotor system of tilting coaxial double-rotor aircraft |
| CN110979653A (en) * | 2019-12-28 | 2020-04-10 | 苏州韬讯航空科技有限公司 | Three-steering-engine coaxial dual-rotor system and control strategy thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181218 |