CN108006203A - A kind of electric control stepless big payload helicopter variable speed gearbox - Google Patents
A kind of electric control stepless big payload helicopter variable speed gearbox Download PDFInfo
- Publication number
- CN108006203A CN108006203A CN201711472512.8A CN201711472512A CN108006203A CN 108006203 A CN108006203 A CN 108006203A CN 201711472512 A CN201711472512 A CN 201711472512A CN 108006203 A CN108006203 A CN 108006203A
- Authority
- CN
- China
- Prior art keywords
- gear
- rotor part
- ring
- power input
- bevel gear
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- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/023—Mounting or installation of gears or shafts in the gearboxes, e.g. methods or means for assembly
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/02—Gearboxes; Mounting gearing therein
- F16H57/038—Gearboxes for accommodating bevel gears
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Structure Of Transmissions (AREA)
Abstract
The present invention provides a kind of electric control stepless big payload helicopter variable speed gearbox,Including main gear reducer,Planet-gear speed reducer,Master control deployment unit and primary transmission mechanism,The main gear reducer includes intermeshing first bevel gear and co-shaft-surface gear,The planet-gear speed reducer includes sun gear and gear ring,The sun gear connects the first bevel gear,Some planetary gears are equipped between the sun gear and the gear ring,The planetary gear is engaged with the sun gear and the gear ring respectively,The master control deployment unit includes the ring gear and ring gear controller being connected with each other,The ring gear is engaged with the gear ring,The level-one rotating mechanism includes power input mechanism and second bevel gear,The power input mechanism is equipped with gear,The gear is engaged with the second bevel gear,The second bevel gear is connected with the sun gear.Its stepless reduction rotating speed is smoothly converted to preferable rotating speed when the present invention makes large-scale unmanned helicopter winged before high speed.
Description
Technical field
The invention belongs to helicopter transmission technology field, and in particular to a kind of electric control stepless big payload helicopter variable speed speed change
Case.
Background technology
Traditional gearbox can show discontinuous problem when variable speed, the problems such as influencing whether the control of helicopter.Specially
A kind of unmanned helicopter of profit or model helicopter gearbox (publication number：CN203421149U it is taper) to disclose a kind of upper casing,
Lower casing is cylinder, and main shaft is passed through from upper casing top down and engaged in lower casing by main tooth with input gear axle, inputs tooth
Wheel shaft coordinates synchronizing wheel on the outside of lower case side wall by unilateral bearing, and input gear the tip of the axis connects tail by shaft joint
Gearbox.The utility model is transmitted to the power of tail no longer by gearbox, eliminates special tail transmission shaft, greatly reduces
Structure member, makes the axis easily fabricated, cost-effective, but easily when rotating speed is changed from high to low in speed change torsion cannot when
Supplement come up, larger impact and other problems can be brought to whole transmission system.
The content of the invention
The object of the present invention is to provide a kind of electric control stepless big payload helicopter variable speed gearbox, solution is large-scale, and nobody goes straight up to
Machine flies state advancing blade stall problem before high speed, its stepless reduces turns when making large-scale unmanned helicopter winged before high speed
Speed is smoothly converted to preferable rotating speed.
The present invention provides following technical solution：
A kind of electric control stepless big payload helicopter variable speed gearbox, including main gear reducer, planet-gear speed reducer, master control allotment
Unit and primary transmission mechanism, the main gear reducer include intermeshing first bevel gear and co-shaft-surface gear, the planet
Wheel gear reducer includes sun gear and gear ring, and the sun gear connects the first bevel gear, the sun gear and the gear ring it
Between be equipped with some planetary gears, the planetary gear is engaged with the sun gear and the gear ring respectively, the master control deployment unit bag
The ring gear and ring gear controller of interconnection are included, the ring gear is engaged with the gear ring, and the level-one rotates
Mechanism includes power input mechanism and second bevel gear, and the power input mechanism is equipped with gear, the gear and described second
Bevel gear engages, and the second bevel gear is connected with the sun gear.
Preferably, the co-shaft-surface gear includes upper rotor part and lower rotor part, and the first bevel gear is located at the upper rotor part
It is intermeshed between the lower rotor part and respectively with the upper rotor part and the lower rotor part.
Preferably, be additionally provided with idle pulley between the upper rotor part and the lower rotor part, the idle pulley respectively with the upper rotor part
It is intermeshed with the lower rotor part.
Preferably, coaxial between the upper rotor part and the lower rotor part is equipped with lower rotor part output shaft, the upper rotor part
Axle center is equipped with upper rotor part output shaft.
Preferably, the planet-gear speed reducer further includes rack, and the planetary gear is located in the rack, the rack with
The gear ring and the first bevel gear are coaxially disposed.
Preferably, the power input mechanism includes the first power input mechanism and the second power input mechanism, and described
One power input mechanism and second power input mechanism are respectively equipped with the gear, the second bevel gear and the sun
Wheel is coaxially disposed.
The beneficial effects of the invention are as follows：Gearbox overall structure is simple, realizes helicopter in height by the engagement between gear
Its stepless reduction rotating speed is smoothly converted to preferable rotating speed when flying before speed；Machine gearbox is gone straight up to compared to traditional, using row
Star wheel reducer, without shifting slide gear during gearshift, therefore fretting wear is small, lasts a long time and simple in structure, compact；Due to being electricity
Planet-gear speed reducer is controlled, gearratio change is continuous, and change procedure is steadily substantially without impact, then gearbox is with efficient, linear
Well, the advantages that controllability is good.
Brief description of the drawings
Attached drawing is used for providing a further understanding of the present invention, and a part for constitution instruction, the reality with the present invention
Apply example to be used to explain the present invention together, be not construed as limiting the invention.In the accompanying drawings：
Fig. 1 is schematic structural view of the invention；
Fig. 2 is side structure schematic view of the present invention；
Fig. 3 is overlooking the structure diagram of the present invention；
Fig. 4 is principle of the invention structure diagram；
In figure mark for：1. main gear reducer；11. upper rotor part；111. upper rotor part output shaft；12. lower rotor part；121. lower rotor part
Output shaft；13. idle pulley；14. first bevel gear；2. planet-gear speed reducer；21. gear ring；22. planetary gear；23. sun gear；24. machine
Frame；3. master control deployment unit；31. ring gear controller；32. ring gear；4. primary transmission mechanism；41. second bevel gear；
42. the first power input mechanism；43. the second power input mechanism.
Embodiment
As Figure 1-Figure 4, a kind of electric control stepless big payload helicopter variable speed gearbox, including main gear reducer 1, planetary gear
Gear reducer 2, master control deployment unit 3 and primary transmission mechanism 4, main gear reducer 1 is including intermeshing first bevel gear 14 and altogether
Axial plane gear, co-shaft-surface gear include upper rotor part 11 and lower rotor part 12, and first bevel gear 14 is located at upper rotor part 11 and lower rotor part 12
Between and be intermeshed respectively with upper rotor part 11 and lower rotor part 12.Idle pulley 13 is additionally provided between upper rotor part 11 and lower rotor part 12, it is lazy
Wheel 13 is intermeshed with upper rotor part 11 and lower rotor part 12 respectively.Coaxial between upper rotor part 11 and lower rotor part 12 is equipped with lower rotor part
Output shaft 121,11 axle center of upper rotor part are equipped with upper rotor part output shaft 111.Planet-gear speed reducer 2 includes sun gear 23 and gear ring
21, sun gear 23 connects first bevel gear 14, some planetary gears 22 is equipped between sun gear 23 and gear ring 21, planetary gear 22 is distinguished
Engaged with sun gear 23 and gear ring 21, master control deployment unit 3 includes the ring gear 32 and ring gear controller being connected with each other
31, ring gear 32 is engaged with gear ring 21, and planet-gear speed reducer 2 further includes rack 24, and planetary gear 22 is located in rack 24, rack
24 are coaxially disposed with gear ring 21 and first bevel gear 14.Level-one rotating mechanism 4 includes power input mechanism and second bevel gear 41,
Power input mechanism is equipped with gear, and gear is engaged with second bevel gear 41, and second bevel gear 41 is connected with sun gear 23.Power is defeated
Entering mechanism includes the first power input mechanism 42 and the second power input mechanism 43, the first power input mechanism 42 and the second power
Input mechanism 43 is respectively equipped with gear, and second bevel gear 41 is coaxially disposed with sun gear 23, is driven.
As Figure 1-Figure 4, in a kind of electric control stepless big payload helicopter variable speed gearbox：Primary transmission mechanism 4, aircraft
Power is inputted by the first power input mechanism 42 and the second power input mechanism 43, and power is realized by two pairs of bevel gear engagements
It is aggregated on same bevel gear, that is, is aggregated into second bevel gear 41；Planet-gear speed reducer 2, the output of primary transmission mechanism 4
Pass to the input sun gear 23 of planet-gear speed reducer 2 from second bevel gear 41, four uniformly distributed planetary gears around sun gear 23
22 unitary rotation is the output of whole planet-gear speed reducer 2, and when input speed is certain, the rotating speed of gear ring 21 controls
The output of planetary gear 22；Master control deployment unit 3, ring gear controller 3 controls ring gear 32 by motor, so that with moving teeth
21 rotating modes are enclosed to control the output of planet-gear speed reducer, so, when 31 rotating speed of ring gear controller increases, gear ring
21 rotating speeds increase, and 2 output speed of planet-gear speed reducer is reduced, and control accuracy depends on the sensitivity of ring gear controller 31；
Main gear reducer 1, planet-gear speed reducer 2 are output in first bevel gear 14 by planetary gear 22, first bevel gear 14 and coaxial
Upper rotor part 11 is engaged with 12 bevel gear of lower rotor part, and the speed of such first bevel gear 14 can be diverted to two same shaft bevel gears
On, and speed solves large-scale unmanned helicopter in height on the contrary, at this moment can realize the power transmission of the coaxial blade of helicopter
Fly state advancing blade stall problem before speed, its stepless reduction rotating speed is smooth when making large-scale unmanned helicopter winged before high speed
It is converted to preferable rotating speed.Further, main gear reducer 1 sets an idle pulley 13 to increase constitutional balance intensity.
Further, due to being planet-gear speed reducer 2, all gears are intermeshed all the time, without shifting slide gear during gearshift,
Therefore fretting wear is small, lasts a long time, simple in structure, compact.
Further, due to there is four uniformly distributed planetary gears 22, its load is assigned on large number of tooth, intensity it is big because
The radial component of reaction force can mutually balance each other between the centrifugal intertia force and flank profil that revolve round the sun and produce, therefore main shaft stress is small, transmit
Power is big；And due to being automatically controlled planet-gear speed reducer 2, gearratio change is continuous, and change procedure is steadily substantially without impact.In addition by
Inside engaged gear is used in it, takes full advantage of the space of transmission, and input and output shaft is point-blank, so whole train
Bulk it is more much smaller than the common ordinary gear train under the same terms.
The foregoing is only a preferred embodiment of the present invention, is not intended to limit the invention, although with reference to foregoing reality
Apply example the present invention is described in detail, for those skilled in the art, it still can be to foregoing each implementation
Technical solution described in example is modified, or carries out equivalent substitution to which part technical characteristic.All essences in the present invention
With within principle, any modification, equivalent replacement, improvement and so on, should all be included in the protection scope of the present invention god.
Claims (6)
1. a kind of electric control stepless big payload helicopter variable speed gearbox, it is characterised in that slow down including main gear reducer, planetary gear
Machine, master control deployment unit and primary transmission mechanism, the main gear reducer include intermeshing first bevel gear and co-shaft-surface tooth
Wheel, the planet-gear speed reducer include sun gear and gear ring, and the sun gear connects the first bevel gear, the sun gear and
Some planetary gears are equipped between the gear ring, the planetary gear is engaged with the sun gear and the gear ring respectively, the master control
Deployment unit includes the ring gear and ring gear controller being connected with each other, and the ring gear is engaged with the gear ring, institute
Stating level-one rotating mechanism includes power input mechanism and second bevel gear, and the power input mechanism is equipped with gear, the gear
Engaged with the second bevel gear, the second bevel gear is connected with the sun gear.
2. a kind of electric control stepless big payload helicopter variable speed gearbox according to claim 1, it is characterised in that described common
Axial plane gear includes upper rotor part and lower rotor part, and the first bevel gear is located between the upper rotor part and the lower rotor part and difference
It is intermeshed with the upper rotor part and the lower rotor part.
3. a kind of electric control stepless big payload helicopter variable speed gearbox according to claim 2, it is characterised in that on described
Idle pulley is additionally provided between rotor and the lower rotor part, the idle pulley is intermeshed with the upper rotor part and the lower rotor part respectively.
4. a kind of electric control stepless big payload helicopter variable speed gearbox according to claim 2, it is characterised in that on described
Coaxial between rotor and the lower rotor part is equipped with lower rotor part output shaft, and the upper rotor part axle center is exported equipped with upper rotor part
Axis.
A kind of 5. electric control stepless big payload helicopter variable speed gearbox according to claim 1, it is characterised in that the row
Star wheel reducer further includes rack, and the planetary gear is located in the rack, the rack and the gear ring and first cone
Gear is coaxially disposed.
6. a kind of electric control stepless big payload helicopter variable speed gearbox according to claim 1, it is characterised in that described dynamic
Power input mechanism includes the first power input mechanism and the second power input mechanism, first power input mechanism and described
Two power input mechanisms are respectively equipped with the gear, and the second bevel gear is coaxially disposed with the sun gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711472512.8A CN108006203A (en) | 2017-12-29 | 2017-12-29 | A kind of electric control stepless big payload helicopter variable speed gearbox |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711472512.8A CN108006203A (en) | 2017-12-29 | 2017-12-29 | A kind of electric control stepless big payload helicopter variable speed gearbox |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108006203A true CN108006203A (en) | 2018-05-08 |
Family
ID=62048881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711472512.8A Pending CN108006203A (en) | 2017-12-29 | 2017-12-29 | A kind of electric control stepless big payload helicopter variable speed gearbox |
Country Status (1)
| Country | Link |
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| CN (1) | CN108006203A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112937881A (en) * | 2021-02-09 | 2021-06-11 | 中国航发哈尔滨东安发动机有限公司 | Face gear transmission coaxial reversing device |
| CN113775702A (en) * | 2021-09-13 | 2021-12-10 | 中国人民解放军国防科技大学 | Meta-cell and large-range variable-stiffness mechanical metamaterial based on planetary gear system |
Citations (8)
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|---|---|---|---|---|
| CN202188076U (en) * | 2011-08-05 | 2012-04-11 | 南京工程学院 | Planetary gear continuously variable transmission |
| CN202914648U (en) * | 2012-12-04 | 2013-05-01 | 何晓荷 | Stepless speed change device for motor speed regulation |
| CN103791047A (en) * | 2014-02-25 | 2014-05-14 | 合肥工业大学 | Variable transmission system for helicopter |
| CN103979108A (en) * | 2014-05-29 | 2014-08-13 | 合肥工业大学 | Main reducer for coaxial dual-rotor high-speed helicopter with tension paddle |
| US20150274287A1 (en) * | 2013-03-15 | 2015-10-01 | Bell Helicopter Textron Inc. | Speed Control Assembly and Methods of Using Same |
| US20170030432A1 (en) * | 2015-07-29 | 2017-02-02 | Sikorsky Aircraft Corporation | Planetary gear sets for power transmissions |
| CN206368946U (en) * | 2016-11-28 | 2017-08-01 | 彭世昌 | Many power planetary mechanism stepless gear systems and buncher |
| CN207830527U (en) * | 2017-12-29 | 2018-09-07 | 江苏方阔航空科技有限公司 | A kind of electric control stepless big payload helicopter variable speed gearbox |
-
2017
- 2017-12-29 CN CN201711472512.8A patent/CN108006203A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202188076U (en) * | 2011-08-05 | 2012-04-11 | 南京工程学院 | Planetary gear continuously variable transmission |
| CN202914648U (en) * | 2012-12-04 | 2013-05-01 | 何晓荷 | Stepless speed change device for motor speed regulation |
| US20150274287A1 (en) * | 2013-03-15 | 2015-10-01 | Bell Helicopter Textron Inc. | Speed Control Assembly and Methods of Using Same |
| CN103791047A (en) * | 2014-02-25 | 2014-05-14 | 合肥工业大学 | Variable transmission system for helicopter |
| CN103979108A (en) * | 2014-05-29 | 2014-08-13 | 合肥工业大学 | Main reducer for coaxial dual-rotor high-speed helicopter with tension paddle |
| US20170030432A1 (en) * | 2015-07-29 | 2017-02-02 | Sikorsky Aircraft Corporation | Planetary gear sets for power transmissions |
| CN206368946U (en) * | 2016-11-28 | 2017-08-01 | 彭世昌 | Many power planetary mechanism stepless gear systems and buncher |
| CN207830527U (en) * | 2017-12-29 | 2018-09-07 | 江苏方阔航空科技有限公司 | A kind of electric control stepless big payload helicopter variable speed gearbox |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112937881A (en) * | 2021-02-09 | 2021-06-11 | 中国航发哈尔滨东安发动机有限公司 | Face gear transmission coaxial reversing device |
| CN113775702A (en) * | 2021-09-13 | 2021-12-10 | 中国人民解放军国防科技大学 | Meta-cell and large-range variable-stiffness mechanical metamaterial based on planetary gear system |
| CN113775702B (en) * | 2021-09-13 | 2023-02-03 | 中国人民解放军国防科技大学 | Meta-cell and large-range variable-stiffness mechanical metamaterial based on planetary gear system |
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| TA01 | Transfer of patent application right |
Effective date of registration: 20211009 Address after: 211100 room 1613, building B5, Jiulong lake international enterprise headquarters park, No. 19, Suyuan Avenue, Jiangning District, Nanjing, Jiangsu Province (Jiangning Development Zone) Applicant after: Nanjing ruilanshi Photoelectric Sensor Technology Research Institute Co.,Ltd. Address before: 210000 No. 1, Dongji Avenue, Jiangning Development Zone, Nanjing, Jiangsu Applicant before: JIANGSU FANGKUO AVIATION TECHNOLOGY Co.,Ltd. |
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