CN106394894B - Helicopter Transmission System - Google Patents
Helicopter Transmission System Download PDFInfo
- Publication number
- CN106394894B CN106394894B CN201610934978.4A CN201610934978A CN106394894B CN 106394894 B CN106394894 B CN 106394894B CN 201610934978 A CN201610934978 A CN 201610934978A CN 106394894 B CN106394894 B CN 106394894B
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- China
- Prior art keywords
- gear
- face gear
- rotor shaft
- roller gear
- roller
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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 kind of Helicopter Transmission Systems, including cylindrical gear drive, cylindrical gear drive includes the first roller gear for exporting power outward, and the output end of the first roller gear is connected with for driving upper rotor on helicopter and lower rotor coaxial line and the power-driven mechanism of different rotation direction rotations.Power-driven mechanism include for installing the interior rotor shaft of rotor, the outer rotor shaft for installing lower rotor, upper rotor is installed in the outer circle of interior rotor shaft, and lower rotor is installed in the outer circle of outer rotor shaft.The input terminal of interior rotor shaft is connected with the first face gear for driving it to rotate, the input terminal of outer rotor shaft is connected with the second face gear for driving it to rotate, first face gear and the second face gear are sequentially arranged up and down, and the first roller gear is set between the first face gear and the second face gear and is engaged respectively from the first face gear and the second face gear to drive the first face gear and the second face gear coaxial line and the rotation of different rotation directions.
Description
Technical field
The present invention relates to power transmission fields, particularly, are related to a kind of Helicopter Transmission System.
Background technique
Transmission system is helicopter key components, and the performance of transmission system directly affects the performance of helicopter, therefore,
Deng Guo Helicopter Corporation, the United States, Russia has put into a large amount of human and material resources and has studied Helicopter Transmission System.
Existing helicopter includes coaxial helicopter, and such as the K50 helicopter of Russia, as traditional coaxial formula are straight
The machine of liter, main transmission realize coaxial output using compound planetary train, and compound planetary train transmission is bigger, carries energy
Power is strong, and but its structure is complex, and the quantity of the parts such as gear, bearing is more, and system reliability is lower.United States Patent (USP) US7413142
The Helicopter Transmission System configuration that a kind of magnetic tape trailer promotes is disclosed, in the transmission system, using the inside and outside engagement realization of roller gear
Coaxial output, structure gear quantity is more, and volume is larger, while because using bevel gear commutation transmission, split bearing is subjected to
Large axial force.
Summary of the invention
The present invention provides a kind of Helicopter Transmission System, with solve existing for existing transmission system structure is complicated, gear,
The quantity of the parts such as bearing is more, volume is big, system reliability is lower and split bearing is subjected to the big technical problem of axial force.
The technical solution adopted by the invention is as follows:
A kind of Helicopter Transmission System, including being used to provide power and making the column gear transmission machine exported after dynamic retarding
Structure, cylindrical gear drive include the first roller gear for exporting power outward, the output end 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 rotations；Power
Driving mechanism include for installing the interior rotor shaft of rotor, the outer rotor shaft for installing lower rotor, in upper rotor is installed in
In the outer circle of rotor shaft, lower rotor is installed in the outer circle of outer rotor shaft；The input terminal of interior rotor shaft is connected with for driving it
First face gear of rotation, the input terminal of outer rotor shaft are connected with the second face gear for driving it to rotate, the second face gear
With the first face gear up and down be sequentially arranged, the first roller gear be set between the first face gear and the second face gear and respectively with
First face gear and the engagement of the second face gear are to drive the first face gear and the second face gear coaxial line and different rotation direction rotations.
Further, outer rotor shaft is the hollow shaft of both ends connection, interior rotor shaft coaxial line be installed in outer rotor shaft and
Outer rotor shaft is stretched out at both ends respectively；Lower rotor is installed in the outer circle on outer rotor shaft top, and the second face gear is installed in outer rotor
In the outer circle of axis bottom end；Upper rotor is installed in the outer circle on interior rotor shaft top, and the first face gear is installed in interior rotor shaft bottom end
Outer circle on.
Further, both the first face gear and the second face gear structure are identical and are arranged in parallel；Under second face gear
Surface is equipped with the second gear ring towards the first face gear, and the upper surface of the first face gear is equipped with the towards the second face gear
One gear ring, the upside of the first roller gear are engaged with the second gear ring, and the downside of the first roller gear is engaged with the first gear ring.
Further, cylindrical gear drive includes a plurality of first order being used to provide power and export dynamic retarding
Driving member, the second level driving member for being exported outward after merging the power of a plurality of first order driving member；A plurality of
The output end of primary transmission component is connected with the input terminal of second level driving member.
Further, second level driving member includes the first roller gear, and the input terminal of the first roller gear is connected with the
Two roller gears；The output end 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, includes power source and the output end with power source
It is connected so that the transmission parts that dynamic retarding exports, the output end of transmission parts are 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 output end of the transmission parts of primary transmission component is connected with the second roller gear respectively.
Further, power source is turboshaft engine.
Further, each transmission parts include the third roller gear being connected with the output end of power source and third cylinder
4th roller gear of gear engagement connection, the 5th roller gear that connection is engaged with the 4th roller gear, the 5th roller gear
It is connect with the second roller gear external toothing.
Further, the first face gear, the second face gear, the first roller gear, the second roller gear, third Cylinder Gear
Wheel, the 4th roller gear and the equal dead axle installation of the 5th roller gear.
The invention has the following advantages:
In transmission system, power is inputted by the first roller gear single line, by the work of the first face gear and the second face gear
By interior rotor shaft and the coaxial dual output of outer rotor shaft after, to realize the coaxial dual output of the single input of power；Entire power train
Power is transmitted by roller gear and face gear in system, and zerol bevel gear, therefore bearing arrangement and casing design are simple, and Cylinder Gear
What the axially mounted precision of wheel did not influenced roller gear and roller gear or face gear engages effect；Transmission system of the invention is adopted
Power is transmitted with roller gear and face gear, is cooperated compared to existing using compound planetary train or roller gear and conical gear
Transfer motion power, structure is simple, small in size, and the part demands such as gear, bearing are few, and installation, disassembling section are simple, drive system
High reliablity, the axial force that split bearing is born are small.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to figure, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations 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 schematic view of the front view of Helicopter Transmission System in Fig. 1.
Marginal data
10, cylindrical gear drive；11, the first roller gear；12, the second roller gear；13, power source；14, third
Roller gear；15, the 4th roller gear；16, the 5th roller gear；20, upper rotor；30, lower rotor；40, power-driven mechanism；
41, interior rotor shaft；42, outer rotor shaft；43, the first face gear；44, the second face gear.
Specific embodiment
The embodiment of the present invention is described in detail below in conjunction with attached drawing, but the present invention can be defined by the claims
Implement with the multitude of different ways of covering.
Referring to Figures 1 and 2, the preferred embodiment of the present invention provides a kind of Helicopter Transmission System, including for providing
Power simultaneously makes the cylindrical gear drive 10 exported after dynamic retarding, cylindrical gear drive 10 include for by power to
First roller gear 11 of outer output, the output end of the first roller gear 11 are connected with for driving the upper rotor 20 on helicopter
With the power-driven mechanism 40 of lower 30 coaxial line of rotor and different rotation direction rotations.Power-driven mechanism 40 includes 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 are installed in the outer circle of interior rotor shaft 41
On, lower rotor 30 is installed in the outer circle of outer rotor shaft 42.The input terminal of interior rotor shaft 41 is connected with for driving it to rotate
First face gear 43, the input terminal of outer rotor shaft 42 are connected with the second face gear 44 for driving it to rotate, the first face gear
43 and second about 44 face gear be sequentially arranged, the first roller gear 11 be set to the first face gear 43 and the second face gear 44 it
Between and engage respectively 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
Line and different rotation direction rotations.
Transmission system work when, cylindrical gear drive 10 provide power and by after dynamic retarding by the first roller gear
11 outward output, since the second face gear 44 and the first about 43 face gear are sequentially arranged, and the first roller gear 11 respectively with
First face gear 43 and the engagement of the second face gear 44, 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 terminal and the of the interior rotor shaft 41 of rotor 20 is installed
One face gear 43 is connected, and the input terminal for being equipped with the outer rotor shaft 42 of lower rotor 30 is connected with the second face gear 44, therefore interior rotor
Axis 41 under the action of the first face gear 43 with outer rotor shaft 42 under the action of the second face gear 44 coaxial line and different rotary
Direction rotates.In transmission system, power is inputted by 11 single line of the first roller gear, by 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, to realize the coaxial dual output of the single input of power；
Power is transmitted by roller gear and face gear in entire transmission system, and zerol bevel gear, therefore bearing arrangement and casing design letter
It is single, and the axially mounted precision of roller gear do not influence roller gear and roller gear or face gear engage effect；The present invention
Transmission system power is transmitted using roller gear and face gear, compared to it is existing using compound planetary train or roller gear with
Conical gear cooperates transfer motion power, and structure is simple, small in size, and the part demands such as gear, bearing are few, installation, disassembling section letter
Single, the axial force of the high reliablity of drive system, split bearing receiving is small.
Optionally, as shown in Figure 1, outer rotor shaft 42 is the hollow shaft of both ends connection, interior 41 coaxial line of rotor shaft is installed in
In outer rotor shaft 42 and outer rotor shaft 42 is stretched out at both ends respectively.Lower rotor 30 is installed in the outer circle on outer 42 top of rotor shaft, the
Two face gears 44 are installed in the outer circle of outer 42 bottom end of rotor shaft.Upper rotor 20 is installed in the outer circle on interior 41 top of rotor shaft,
First face gear 43 is installed in the outer circle of interior 41 bottom end of rotor shaft.In the present embodiment, for the weight for mitigating helicopter, interior rotor
Axis 41 is also the hollow shaft of both ends connection.
In the present embodiment, as shown in Fig. 2, both the first face gear 43 and second face gears 44 structure is identical and parallel sets
It sets.The lower surface of second face gear 44 is equipped with the second gear ring towards the first face gear 43, the upper surface of the first face gear 43
It is equipped with the first gear ring towards the second face gear 44, the upside of the first roller gear 11 is engaged with the second gear ring, the first cylinder
It is engaged with the first gear ring the downside of gear 11.
Optionally, cylindrical gear drive 10 includes a plurality of first order being used to provide power and export dynamic retarding
Driving member, the second level driving member for being exported outward after merging the power of a plurality of first order driving member.A plurality of
The output end of primary transmission component is connected with the input terminal 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 terminal be connected with the second roller gear 12.The output end of a plurality of first order driving member respectively with 12 phase of the second roller gear
Even.
In the present embodiment, as shown in Figure 1, the structure of a plurality of first order driving member is identical, include power source 13 and with
The output end of power source 13 is connected so that the transmission parts that dynamic retarding exports, the output end of transmission parts and the second roller gear
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 output end of the transmission parts 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 be it is a plurality of, a plurality of first order driving member is successively arranged in parallel, and a plurality of the
The output end of the transmission parts of primary transmission component is connected with the second roller gear 12 respectively.
In this specific embodiment, as shown in Figure 1, each transmission parts include the third circle being connected with the output end of power source 13
Stud wheel 14, engages connection with the 4th roller gear 15 at the 4th roller gear 15 that connection is engaged with third roller gear 14
5th roller gear 16, the 5th roller gear 16 are connect with 12 external toothing of the second roller gear.
Preferably, the first face gear 43, the second face gear 44, the first roller gear 11, the second roller gear 12, third circle
Stud wheel 14, the 4th roller gear 15 and the equal dead axle installation of the 5th roller gear 16.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of Helicopter Transmission System, which is characterized in that
Including being used to provide power and making the cylindrical gear drive (10) exported after dynamic retarding, the column gear transmission
Mechanism (10) includes the first roller gear (11) for exporting power outward, the output end of 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 rotations
Mechanism (40)；
The power-driven mechanism (40) include for installing the interior rotor shaft (41) of the upper rotor (20), it is described for installing
The outer rotor shaft (42) of lower rotor (30), the upper rotor (20) is installed in the outer circle of the interior rotor shaft (41), under described
Rotor (30) is installed in the outer circle of the outer rotor shaft (42)；
The input terminal of the interior rotor shaft (41) is connected with the first face gear (43) for driving it to rotate, the outer rotor shaft
(42) input terminal is connected with the second face gear (44) for driving it to rotate, second face gear (44) and described first
Face gear (43) is sequentially arranged up and down, and first roller gear (11) is set to first face gear (43) and described second
It is engaged between face gear (44) and respectively with first face gear (43) and second face gear (44) to drive described
One face gear (43) and the second face gear (44) coaxial line and different rotation direction rotations.
2. Helicopter Transmission System according to claim 1, which is characterized in that
The outer rotor shaft (42) is the hollow shaft of both ends connection, and interior rotor shaft (41) coaxial line is installed in the outer rotor
In axis (42) and the outer rotor shaft (42) is stretched out at both ends respectively；
The lower rotor (30) is installed in the outer circle on outer rotor shaft (42) top, and second face gear (44) is installed in
In the outer circle of outer rotor shaft (42) bottom end；
The upper rotor (20) is installed in the outer circle on interior rotor shaft (41) top, and first face gear (43) is installed in
In the outer circle of interior rotor shaft (41) bottom end.
3. Helicopter Transmission System according to claim 2, which is characterized in that
First face gear (43) is identical with the second face gear (44) the two structure and is arranged in parallel；
The lower surface of second face gear (44) be equipped with towards first face gear (43) the second gear ring, described first
The upper surface of face gear (43) is equipped with the first gear ring towards second face gear (44), first roller gear (11)
Upside engaged with second gear ring, the downside of first roller gear (11) is engaged with first gear ring.
4. Helicopter Transmission System according to claim 1, which is characterized in that
The cylindrical gear drive (10) includes a plurality of first order transmission for being used to provide power and exporting dynamic retarding
Component, the second level driving member for being exported outward after merging the power of a plurality of first order driving member；
The output end of a plurality of first order driving member is connected with the input terminal of the second level driving member.
5. Helicopter Transmission System according to claim 4, which is characterized in that
The second level driving member includes first roller gear (11), and the input terminal of first roller gear (11) connects
It is connected to the second roller gear (12)；
The output end of a plurality of first order driving member is connected with second roller gear (12) respectively.
6. Helicopter Transmission System according to claim 5, which is characterized in that
The structure of a plurality of first order driving member is identical, includes power source (13) and the output with the power source (13)
End is connected so that the transmission parts that dynamic retarding exports, the output end of the transmission parts and the second roller gear (12) phase
Even.
7. Helicopter Transmission System according to claim 6, which is characterized in that
The quantity of the first order driving member is two, and two first order driving members are arranged in parallel, two articles described the
The output end of the transmission parts of primary transmission component is connected with second roller gear (12) respectively.
8. Helicopter Transmission System according to claim 6, which is characterized in that
The power source (13) is turboshaft engine.
9. Helicopter Transmission System according to claim 6, which is characterized in that
Each transmission parts include the third roller gear (14) being connected with the output end of the power source (13), with described the
4th roller gear (15) of three roller gears (14) engagement connection engages the 5th of connection with the 4th roller gear (15)
Roller gear (16), the 5th roller gear (16) connect with the second roller gear (12) external toothing.
10. Helicopter Transmission System according to claim 9, which is characterized in that
First face gear (43), second face gear (44), first roller gear (11), second Cylinder Gear
Take turns (12), the third roller gear (14), the 4th roller gear (15) and the equal dead axle of the 5th roller gear (16)
Installation.
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 CN106394894A (en) | 2017-02-15 |
| CN106394894B true 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 |
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| CN (1) | CN106394894B (en) |
Families Citing this family (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 |
| CN110094465B (en) * | 2019-05-14 | 2024-06-14 | 北京辐全智能科技股份有限公司 | Speed reducer |
| 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 |
Citations (5)
| 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 |
| 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 |
| CN105650206A (en) * | 2016-03-31 | 2016-06-08 | 中国航空动力机械研究所 | Helicopter transmission device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2922191B1 (en) * | 2007-10-12 | 2010-06-11 | Infotron | TWO ROTORS FLYING ENGINE |
-
2016
- 2016-11-01 CN CN201610934978.4A patent/CN106394894B/en active Active
Patent Citations (5)
| 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 |
| 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 |
| CN105650206A (en) * | 2016-03-31 | 2016-06-08 | 中国航空动力机械研究所 | Helicopter transmission device |
Also Published As
| Publication number | Publication date |
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| CN106394894A (en) | 2017-02-15 |
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