CN106394894A - Helicopter transmission system - Google Patents
Helicopter transmission system Download PDFInfo
- Publication number
- CN106394894A CN106394894A CN201610934978.4A CN201610934978A CN106394894A CN 106394894 A CN106394894 A CN 106394894A CN 201610934978 A CN201610934978 A CN 201610934978A CN 106394894 A CN106394894 A CN 106394894A
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- CN
- China
- Prior art keywords
- gear
- face gear
- roller gear
- rotor shaft
- face
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gear Transmission (AREA)
- Retarders (AREA)
Abstract
The invention discloses a helicopter transmission system. The helicopter transmission system comprises a cylinder gear transmission mechanism. The cylinder gear transmission mechanism comprises a first cylinder gear used for outputting power outwards. The output end of the first cylinder gear is connected with a power drive mechanism used for driving upper rotor wings and lower rotor wings on a helicopter to coaxially rotate in the different rotating directions. The power drive mechanism comprises an inner rotor wing shaft used for installing the upper rotor wings and an outer rotor wing shaft used for installing the lower rotor wings. The upper rotor wings are arranged on the outer circle of the inner rotor wing shaft, and the lower rotor wings are arranged on the outer circle of the outer rotor wing shaft. The input end of the inner rotor wing shaft is connected with a first face gear used for driving the inner rotor wing shaft to rotate. The input end of the outer rotor wing shaft is connected with a second face gear used for driving the outer rotor wing shaft to rotate. The first face gear and the second face gear are vertically and sequentially arranged. The first cylinder gear is arranged between the first face gear and the second face gear and engaged with the first face gear and the second face gear so as to drive the first face gear and the second face gear to coaxially rotate in the different rotating directions.
Description
Technical field
The present invention relates to power transmission field, especially, it is related to a kind of Helicopter Transmission System.
Background technology
Drive system is helicopter key components, and the performance of drive system directly affects the performance of helicopter, therefore,
Deng Guo Helicopter Corporation of the United States, Russia has all put into substantial amounts of human and material resources and Helicopter Transmission System has been studied.
Existing helicopter includes coaxial helicopter, such as Muscovite K50 helicopter, and as traditional coaxial formula is straight
The machine of liter, its main transmission realizes coaxial output using compound planetary train, and this compound planetary train gear ratio is larger, carries energy
Power is strong, but its complex structure, and the quantity of the part such as gear, bearing is more, and system reliability is relatively low.United States Patent (USP) US7413142
Disclose a kind of Helicopter Transmission System configuration of magnetic tape trailer propulsion, in this drive system, realized using the inside and outside engagement of roller gear
Coaxial output, its structure gear quantity is more, and volume is larger, is driven because being commutated using bevel gear, split bearing is subjected to simultaneously
Large axial force.
Content of the invention
The invention provides a kind of Helicopter Transmission System, with solve complex structure, gear that existing drive system exists,
The quantity of the parts such as bearing is more, volume is big, system reliability is relatively low and split bearing is subjected to the big technical problem of axial force.
The technical solution used in the present invention is as follows：
A kind of Helicopter Transmission System, including for providing power and making the column gear transmission machine exporting after dynamic retarding
Structure, cylindrical gear drive includes the first roller gear for outwards exporting power, the outfan of the first roller gear
It is connected with the power-driven mechanism for driving upper rotor on helicopter and lower rotor coaxial line and different rotation direction rotation；Power
Drive mechanism include for install rotor interior rotor shaft, for installing the outer rotor shaft of lower rotor, in upper rotor is installed in
Rotor shaft cylindrical on, lower rotor be installed in outer rotor shaft cylindrical on；The input of interior rotor shaft is connected with for driving it
First face gear of rotation, the input of outer rotor shaft is connected with the second face gear for driving its rotation, the second face gear
Be sequentially arranged up and down with the first face gear, the first roller gear be arranged between the first face gear and the second face gear and respectively with
First face gear and the second face gear engagement are to drive the first face gear and the second face gear coaxial line and different rotation direction rotation.
Further, the hollow axle that outer rotor shaft connects for two ends, interior rotor shaft coaxial line be installed in outer rotor shaft and
Outer rotor shaft is stretched out at two ends respectively；Lower rotor be installed in outer rotor shaft top cylindrical on, the second face gear is installed in outer rotor
Axle bottom cylindrical on；Upper rotor be installed in interior rotor shaft top cylindrical on, the first face gear is installed in interior rotor shaft bottom
Cylindrical on.
Further, the first face gear and the second face gear structure are identical and be arranged in parallel；Under second face gear
Second gear ring of the first face gear is provided with surface, the upper surface of the first face gear is provided with the of the second face gear
One gear ring, the upper side and lower side of the first roller gear is engaged with the second gear ring and the first gear ring respectively.
Further, cylindrical gear drive includes a plurality of first order for providing power and making dynamic retarding export
Driving member, the second level driving member for outwards output after making the power of a plurality of first order driving member merge；A plurality of
The outfan of primary transmission component is all connected with the input of second level driving member.
Further, second level driving member includes the first roller gear, and the input of the first roller gear is connected with
Two roller gears；The outfan of a plurality of first order driving member is connected with the second roller gear respectively.
Further, the structure of a plurality of first order driving member is identical, all includes power source and the outfan with power source
It is connected so that the drive disk assembly of dynamic retarding output, the outfan of drive disk assembly is connected with the second roller gear.
Further, the quantity of first order driving member is two, and two first order driving members are arranged in parallel, two articles the
The outfan of the drive disk assembly of primary transmission component is connected with the second roller gear respectively.
Further, power source is turboshaft engine.
Further, each drive disk assembly includes the 3rd roller gear being connected with the outfan of power source and the 3rd cylinder
The 5th roller gear that the 4th roller gear that gear engagement connects is connected with the 4th roller gear engagement, the 5th roller gear
It is connected with the second roller gear external toothing.
Further, the first face gear, the second face gear, the first roller gear, the second roller gear, the 3rd Cylinder Gear
Wheel, the 4th roller gear and the equal dead axle of the 5th roller gear are installed.
The invention has the advantages that：
In drive system, power is inputted by the first roller gear single line, through the work of the first face gear and the second face gear
With after by interior rotor shaft and the coaxial dual output of outer rotor shaft, thus the coaxial dual output of single input realizing power；Whole power train
In system, power is transmitted by roller gear dough-making powder gear, and zerol bevel gear, therefore bearing arrangement and casing design are simple, and Cylinder Gear
What the axially mounted precision of wheel did not affect roller gear and roller gear or face gear engages effect；The drive system of the present invention is adopted
Transmit power with roller gear dough-making powder gear, compare existing employing compound planetary train or roller gear and coordinate with conical gear
Transfer motion power, its structure is simple, small volume, and the part demand such as gear, bearing is few, and installation, disassembling section are simple, drive system
Reliability is high, and the axial force that split bearing bears is little.
In addition to objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to figure, the present invention is further detailed explanation.
Brief description
The accompanying drawing constituting the part of the application is used for providing a further understanding of the present invention, the schematic reality of the present invention
Apply example and its illustrate, for explaining the present invention, not constituting inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the space structure schematic diagram of the Helicopter Transmission System of the preferred embodiment of the present invention；
Fig. 2 is the main structure diagram of Helicopter Transmission System in Fig. 1.
Marginal data
10th, cylindrical gear drive；11st, the first roller gear；12nd, the second roller gear；13rd, power source；14th, the 3rd
Roller gear；15th, the 4th roller gear；16th, the 5th roller gear；20th, upper rotor；30th, lower rotor；40th, power-driven mechanism；
41st, interior rotor shaft；42nd, outer rotor shaft；43rd, the first face gear；44th, the second face gear.
Specific embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, but the present invention can be defined by the claims
Implement with the multitude of different ways covering.
See figures.1.and.2, the preferred embodiments of the present invention provide a kind of Helicopter Transmission System, including for providing
Power and after making dynamic retarding output cylindrical gear drive 10, cylindrical gear drive 10 include for by power to
First roller gear 11 of outer output, the outfan of the first roller gear 11 is connected with for driving the upper rotor 20 on helicopter
With lower rotor 30 coaxial line and the rotation of different rotation direction power-driven mechanism 40.Power-driven mechanism 40 is included for installing rotation
The interior rotor shaft 41 of the wing 20, the outer rotor shaft 42 for installing lower rotor 30, upper rotor 20 is installed in the cylindrical of interior rotor shaft 41
On, lower rotor 30 be installed in outer rotor shaft 42 cylindrical on.The input of interior rotor shaft 41 is connected with for driving its rotation
First face gear 43, the input of outer rotor shaft 42 is connected with the second face gear 44 for driving its rotation, the first face gear
43 and second face gear be sequentially arranged about 44, the first roller gear 11 be arranged at the first face gear 43 and the second face gear 44 it
Between and engage with the first face gear 43 and the second face gear 44 to drive the first face gear 43 and the second face gear 44 coaxial respectively
Line and different rotation direction rotation.
Drive system work when, cylindrical gear drive 10 provide power and by after dynamic retarding by the first roller gear
11 outwards export, because the second face gear 44 and the first face gear are sequentially arranged about 43, and the first roller gear 11 respectively with
First face gear 43 and the second face gear 44 engage, therefore the first face gear 43 and the second face gear 44 will be in the first roller gears 11
Driving under coaxial line but different rotary direction rotate, and because the input of interior rotor shaft 41 and the of rotor 20 is installed
One face gear 43 is connected, and the input of outer rotor shaft 42 being provided with lower rotor 30 is connected with the second face gear 44, therefore interior rotor
Axle 41 in the presence of the first face gear 43 with outer rotor shaft 42 in the presence of the second face gear 44 coaxial line and different rotary
Direction rotates.In drive system, power is inputted by the first roller gear 11 single line, through the first face gear 43 and the second face gear
By interior rotor shaft 41 and the coaxial dual output of outer rotor shaft 42 after 44 effect, thus the coaxial dual output of single input realizing power；
In whole drive system, power is transmitted by roller gear dough-making powder gear, and zerol bevel gear, therefore bearing arrangement and casing design letter
Single, and the axially mounted precision of roller gear do not affect roller gear and roller gear or face gear engage effect；The present invention
Drive system adopt roller gear dough-making powder gear to transmit power, compare existing employing compound planetary train or roller gear with
Conical gear coordinates transfer motion power, and its structure is simple, small volume, and the part demand such as gear, bearing is few, installation, disassembling section letter
Single, the reliability of drive system is high, and the axial force that split bearing bears is little.
Alternatively, as shown in figure 1, the hollow axle that connects for two ends of outer rotor shaft 42, interior rotor shaft 41 coaxial line is installed in
Outer rotor shaft 42 is interior and outer rotor shaft 42 is stretched out at two ends respectively.Lower rotor 30 be installed in outer rotor shaft 42 top cylindrical on,
Two face gears 44 be installed in outer rotor shaft 42 bottom cylindrical on.Upper rotor 20 be installed in interior rotor shaft 41 top cylindrical on,
First face gear 43 be installed in interior rotor shaft 41 bottom cylindrical on.In the present embodiment, for mitigating the weight of helicopter, interior rotor
The axle 41 also hollow axle for two ends connection.
In the present embodiment, as shown in Fig. 2 the first face gear 43 is identical with both the second face gears 44 structure and parallel sets
Put.Second gear ring of the first face gear 43, the upper surface of the first face gear 43 are provided with the lower surface of the second face gear 44
On be provided with the first gear ring of the second face gear 44, the upper side and lower side of the first roller gear 11 respectively with the second gear ring and
One gear ring engagement.
Alternatively, cylindrical gear drive 10 includes a plurality of first order for providing power and making dynamic retarding export
Driving member, the second level driving member for outwards output after making the power of a plurality of first order driving member merge.A plurality of
The outfan of primary transmission component is all connected with the input of second level driving member.
In the present embodiment, as shown in figure 1, second level driving member includes the first roller gear 11, the first roller gear 11
Input be connected with the second roller gear 12.The outfan of a plurality of first order driving member respectively with the second roller gear 12 phase
Even.
In the present embodiment, as shown in figure 1, the structure of a plurality of first order driving member is identical, all include power source 13 and with
The outfan of power source 13 is connected so that drive disk assembly, the outfan of drive disk assembly and second roller gear of dynamic retarding output
12 are connected.Preferably, power source 13 is turboshaft engine.
In this specific embodiment, as shown in Fig. 2 the quantity of first order driving member is two, two first order are driven structure
Part is arranged in parallel, and the outfan of the drive disk assembly of two first order driving members is connected with the second roller gear 12 respectively.At it
In its embodiment, the quantity of first order driving member is a plurality of, and a plurality of first order driving member is arranged in parallel successively, and a plurality of the
The outfan of the drive disk assembly of primary transmission component is connected with the second roller gear 12 respectively.
In this specific embodiment, as shown in figure 1, each drive disk assembly includes the 3rd circle being connected with the outfan of power source 13
The 4th roller gear 15 that stud wheel 14 is connected with the 3rd roller gear 14 engagement is connected with the 4th roller gear 15 engagement
5th roller gear 16, the 5th roller gear 16 is connected with the second roller gear 12 external toothing.
Preferably, the first face gear 43, the second face gear 44, the first roller gear 11, the second roller gear the 12, the 3rd circle
Stud wheel 14, the 4th roller gear 15 and the equal dead axle of the 5th roller gear 16 are installed.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.All within the spirit and principles in the present invention, made any repair
Change, equivalent, improvement etc., should be included within the scope of the present invention.
Claims (10)
1. a kind of Helicopter Transmission System it is characterised in that
Including for providing power and making the cylindrical gear drive (10) exporting after dynamic retarding, described column gear transmission
Mechanism (10) includes the first roller gear (11) for outwards exporting power, the outfan of described first roller gear (11)
It is connected with the power drive for driving upper rotor (20) on helicopter and lower rotor (30) coaxial line and different rotation direction rotation
Mechanism (40)；
Described power-driven mechanism (40) include for described upper rotor (20) is installed interior rotor shaft (41), be used for installing described
The outer rotor shaft (42) of lower rotor (30), described upper rotor (20) be installed in described interior rotor shaft (41) cylindrical on, described under
Rotor (30) be installed in described outer rotor shaft (42) cylindrical on；
The input of described interior rotor shaft (41) is connected with the first face gear (43) for driving its rotation, described outer rotor shaft
(42) input is connected with the second face gear (44) for driving its rotation, described second face gear (44) and described first
Face gear (43) is sequentially arranged up and down, and described first roller gear (11) is arranged at described first face gear (43) and described second
Between face gear (44) and engage to drive described respectively with described first face gear (43) and described second face gear (44)
One face gear (43) and described second face gear (44) coaxial line and different rotation direction rotation.
2. Helicopter Transmission System according to claim 1 it is characterised in that
The hollow axle that described outer rotor shaft (42) connects for two ends, described interior rotor shaft (41) coaxial line is installed in described outer rotor
Axle (42) is interior and described outer rotor shaft (42) is stretched out at two ends respectively；
Described lower rotor (30) be installed in described outer rotor shaft (42) top cylindrical on, described second face gear (44) is installed in
Described outer rotor shaft (42) bottom cylindrical on；
Described upper rotor (20) be installed in described interior rotor shaft (41) top cylindrical on, described first face gear (43) is installed in
Described interior rotor shaft (41) bottom cylindrical on.
3. Helicopter Transmission System according to claim 2 it is characterised in that
Both structures of described first face gear (43) and described second face gear (44) are identical and be arranged in parallel；
Second gear ring of described first face gear (43) is provided with the lower surface of described second face gear (44), described first
First gear ring of described second face gear (44), described first roller gear (11) are provided with the upper surface of face gear (43)
The upper side and lower side engage with described second gear ring and described first gear ring respectively.
4. Helicopter Transmission System according to claim 1 it is characterised in that
Described cylindrical gear drive (10) includes a plurality of first order transmission for providing power and make dynamic retarding export
Component, the second level driving member for outwards output after making the power of a plurality of described first order driving member merge；
The outfan of a plurality of described first order driving member is all connected with the input of described second level driving member.
5. Helicopter Transmission System according to claim 4 it is characterised in that
Described second level driving member includes described first roller gear (11), and the input of described first roller gear (11) is even
It is connected to the second roller gear (12)；
The outfan of a plurality of described first order driving member is connected with described second roller gear (12) respectively.
6. Helicopter Transmission System according to claim 5 it is characterised in that
The structure of a plurality of described first order driving member is identical, all includes power source (13) and the output with described power source (13)
End be connected so that dynamic retarding output drive disk assembly, the outfan of described drive disk assembly and described second roller gear (12) phase
Even.
7. Helicopter Transmission System according to claim 6 it is characterised in that
The quantity of described first order driving member is two, and two described first order driving members are arranged in parallel, two articles described the
The outfan of the described drive disk assembly of primary transmission component is connected with described second roller gear (12) respectively.
8. Helicopter Transmission System according to claim 6 it is characterised in that
Described power source (13) is turboshaft engine.
9. Helicopter Transmission System according to claim 6 it is characterised in that
Each described drive disk assembly includes the 3rd roller gear (14) being connected with the outfan of described power source (13) and described
The 4th roller gear (15) that three roller gears (14) engagement connects engages, with described 4th roller gear (15), the 5th being connected
Roller gear (16), described 5th roller gear (16) is connected with the external toothing of described second roller gear (12).
10. Helicopter Transmission System according to claim 9 it is characterised in that
Described first face gear (43), described second face gear (44), described first roller gear (11), described second Cylinder Gear
Wheel (12), described 3rd roller gear (14), described 4th roller gear (15) and described 5th roller gear (16) all dead axles
Install.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610934978.4A CN106394894B (en) | 2016-11-01 | 2016-11-01 | Helicopter Transmission System |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610934978.4A CN106394894B (en) | 2016-11-01 | 2016-11-01 | Helicopter Transmission System |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106394894A true CN106394894A (en) | 2017-02-15 |
| CN106394894B CN106394894B (en) | 2019-04-09 |
Family
ID=58012033
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610934978.4A Active CN106394894B (en) | 2016-11-01 | 2016-11-01 | Helicopter Transmission System |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106394894B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107559383A (en) * | 2017-07-18 | 2018-01-09 | 南京航空航天大学 | A kind of coaxial rotor transmission device with power dividing twice |
| CN110094465A (en) * | 2019-05-14 | 2019-08-06 | 北京辐全智能科技股份有限公司 | Retarder |
| CN110683042A (en) * | 2019-11-11 | 2020-01-14 | 天津工业大学 | Coaxial double-oar eight rotor crafts |
| CN111483590A (en) * | 2020-05-26 | 2020-08-04 | 清华大学 | Coaxial contra-rotating dual-rotor speed reduction transmission structure |
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| US7413142B2 (en) * | 2005-05-31 | 2008-08-19 | Sikorsky Aircraft Corporation | Split torque gearbox for rotary wing aircraft with translational thrust system |
| CN101708774A (en) * | 2009-12-02 | 2010-05-19 | 南京航空航天大学 | Combined shunting mechanism for transmission of face gears and herringbone gears of helicopter main transmission systems |
| US20110024554A1 (en) * | 2007-10-12 | 2011-02-03 | Infotron | Twin rotor flying vehicle |
| CN103072689A (en) * | 2013-01-28 | 2013-05-01 | 黄春水 | Low-rotating-speed double-layer propcopter |
| CN105292458A (en) * | 2015-11-20 | 2016-02-03 | 黑龙江科技大学 | Multi-rotor aircraft dual bevel gear dynamic transmission system |
| CN105650206A (en) * | 2016-03-31 | 2016-06-08 | 中国航空动力机械研究所 | Helicopter transmission device |
-
2016
- 2016-11-01 CN CN201610934978.4A patent/CN106394894B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7413142B2 (en) * | 2005-05-31 | 2008-08-19 | Sikorsky Aircraft Corporation | Split torque gearbox for rotary wing aircraft with translational thrust system |
| US20110024554A1 (en) * | 2007-10-12 | 2011-02-03 | Infotron | Twin rotor flying vehicle |
| CN101708774A (en) * | 2009-12-02 | 2010-05-19 | 南京航空航天大学 | Combined shunting mechanism for transmission of face gears and herringbone gears of helicopter main transmission systems |
| CN103072689A (en) * | 2013-01-28 | 2013-05-01 | 黄春水 | Low-rotating-speed double-layer propcopter |
| CN105292458A (en) * | 2015-11-20 | 2016-02-03 | 黑龙江科技大学 | Multi-rotor aircraft dual bevel gear dynamic transmission system |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107559383A (en) * | 2017-07-18 | 2018-01-09 | 南京航空航天大学 | A kind of coaxial rotor transmission device with power dividing twice |
| CN110094465A (en) * | 2019-05-14 | 2019-08-06 | 北京辐全智能科技股份有限公司 | Retarder |
| CN110683042A (en) * | 2019-11-11 | 2020-01-14 | 天津工业大学 | Coaxial double-oar eight rotor crafts |
| CN110683042B (en) * | 2019-11-11 | 2023-11-24 | 天津工业大学 | Coaxial double-oar eight rotor crafts |
| CN111483590A (en) * | 2020-05-26 | 2020-08-04 | 清华大学 | Coaxial contra-rotating dual-rotor speed reduction transmission structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106394894B (en) | 2019-04-09 |
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