CN211943722U - Face gear coaxial type dual-rotor transmission mechanism with quartic power splitting - Google Patents
Face gear coaxial type dual-rotor transmission mechanism with quartic power splitting Download PDFInfo
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- CN211943722U CN211943722U CN202020221906.7U CN202020221906U CN211943722U CN 211943722 U CN211943722 U CN 211943722U CN 202020221906 U CN202020221906 U CN 202020221906U CN 211943722 U CN211943722 U CN 211943722U
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Abstract
The utility model discloses a face gear coaxial type dual rotor drive mechanism with quartic power split. The main reducer is mainly applied to a main reducer of a helicopter and comprises a grading input part and a shunting output part; firstly, the power of an engine is input into a system through power and is input into a straight spur gear, and the power of the engine is converged into a coaxial face gear supported by a thrust bearing through three-level three-time flow division to realize reversing and power transmission; and finally, the power split output is realized through an output shaft fixedly connected with the face gear and a straight gear meshed with the face gear. Drive mechanism adopts quartic power split configuration, has promoted transmission system's bearing capacity, has compact structure simultaneously, and the quality is light, characteristics such as the reliability is high and drive ratio is big.
Description
Technical Field
The utility model relates to a power transmission system of helicopter, concretely relates to face gear coaxial type dual rotor drive mechanism with quartic power split.
Background
The composite high-speed helicopter is a great development trend of the current high-speed helicopters, and the typical configuration of the composite high-speed helicopter is a coaxial constant-speed counter-rotating double-rotor structure with a tail rotor, wherein the double rotors are used as a lifting system of the helicopter, and the tail rotor is used as a forward-flying propulsion system of the helicopter. The main rotor system of the coaxial contra-rotating double-rotor combined high-speed helicopter is formed by two pairs of rigid blades which coaxially rotate reversely, so that the bidirectional output of system power is realized.
The existing coaxial reverse rotation dual-output transmission system mainly comprises three types of cylindrical gear internal and external meshing transmission, bevel gear transmission and compound planetary transmission.
The transmission system of the novel X2 composite thrust verifier published in 2005 by the West Kesky company adopts cylindrical gears for internal and external meshing transmission, and is characterized in that all gears are fixed-shaft transmission and are limited by structure and bearing capacity. The bevel gear is in a coaxial output structure, the scheme is simple in structure, free of power splitting and limited in bearing capacity.
The compound planet coaxial transmission is applied to helicopter transmission systems such as card-50 and the like designed by Russian Schaft design Bureau, the coaxial reverse output of a rotor shaft is realized through closed differential, but the problems of large number of parts, large volume, difficult design, processing and assembly and the like exist.
The final stage of the transmission structure of the main reducer for the helicopter in the western costas patent US 8870538B2 realizes coaxial reverse rotation and double output through a face gear, has a large transmission ratio, and has the problems of low transmission efficiency, insufficient system strength and the like.
Although high-speed elevators of compound type configuration have been widely used, they still have disadvantages and need to be improved from the core part of the transmission system.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides a solve coaxial constant speed contra-rotating dual rotor configuration helicopter bearing capacity that prior art exists little, the low scheduling problem of reliability, provide a face gear coaxial type dual rotor drive mechanism with quartic power split.
For solving the problems existing in the prior art, the technical scheme of the utility model is that: face gear is coaxial to changeing two rotor drive mechanism, its characterized in that: comprises a hierarchical input part and an output part; the grading input part comprises a three-level fixed-axis gear train consisting of I-level gear transmission, II-level gear transmission and III-level gear transmission;
the I-stage gear transmission comprises a power input gear and two I-stage face gears, and the power input gear is meshed with the two I-stage face gears to realize first-stage transmission;
the II-stage gear transmission comprises two II-stage small cylindrical gears and four II-stage large cylindrical gears; each II-stage small cylindrical gear is coaxial with one I-stage face gear and is simultaneously meshed with two II-stage large cylindrical gears to realize secondary transmission;
the III-level gear transmission comprises four III-level small cylindrical gears and eight III-level large cylindrical gears, each III-level small cylindrical gear is coaxial with one II-level large cylindrical gear and is meshed with two III-level large cylindrical gears simultaneously, and three-level transmission is realized;
the output part comprises back-to-back upper and lower gears; the upper gear is meshed with four III-level large cylindrical gears and is fixedly connected with an upper output shaft; and the lower gear is meshed with the remaining four III-level large cylindrical gears and is fixedly connected with the lower output shaft to finish power output.
Furthermore, the upper gear is meshed with the upper tail wing cylindrical gear, and the lower gear is meshed with the lower tail wing cylindrical gear.
Further, a thrust bearing is arranged between the upper gear and the lower gear.
Furthermore, the upper output shaft and the lower output shaft are hollow shafts, the lower output shaft penetrates through the center of the upper output shaft and is higher than the upper output shaft, and the rotation directions of the upper output shaft and the lower output shaft are opposite and the same speed.
Further, the number of the grading input parts is at least 1, and when multi-path input is adopted, each path has the same configuration and is uniformly arranged along the circumference.
Compared with the prior art, the utility model has the advantages as follows:
1) the utility model combines the two configurations of torque division transmission and face gear transmission, reduces the gear transmission torque, improves the bearing capacity of the system, and simultaneously leads the system structure to be compact and reduces the system quality;
2) the utility model adopts the coaxial configuration of the face gear, compared with the configuration of the closed differential planetary gear train, the rotation speed of the upper rotor and the lower rotor is easy to be completely equal, and the rotation speed of the upper rotor and the lower rotor is difficult to be completely equal due to the difficulty of tooth matching in the configuration of the closed differential planetary gear train;
3) the utility model realizes the functions of speed reduction and reversing of power simultaneously through the coaxial face gear supported by the thrust bearing, and compared with the traditional configuration adopting a bevel gear reversing mechanism, the utility model has the advantages of simple structure, convenient installation and good stability;
4) the last stage of the utility model uses the coaxial face gear with larger size, so that the diameter of the upper and lower output shafts can be designed to be larger, and related devices such as an inner control device, an anti-icing device, a test device and the like can be more easily arranged in the lower output shaft, and the inner diameter of the inner shaft can not be designed to be larger because the closed differential planetary gear train is limited by the size of the sun gear;
5) the utility model discloses from the overall dimension, the drive mechanism profile of sealing differential planetary gear train configuration is more slender, the utility model discloses a drive mechanism profile is then more flat, therefore the accessible improves its mounting platform's high position, increases the under-deck space of helicopter.
6) The utility model discloses upper and lower output shaft power take off is as the ascending power of helicopter, and upper and lower fin gear power take off is as the propulsive power of helicopter, and the flight power demand of satisfying the helicopter that can be better promotes flying speed.
Description of the drawings:
fig. 1 is a schematic structural diagram of a face gear coaxial constant-speed contra-rotating dual-rotor transmission mechanism with four power splitting input by a single engine according to the present invention;
FIG. 2 is a side view of the dual engine input face gear coaxial constant speed counter-rotating dual rotor transmission with four power splits of the present invention;
FIG. 3 is a top view of the dual engine input face gear coaxial constant speed counter-rotating dual rotor transmission with four power splits of the present invention;
fig. 4 is a schematic structural diagram of the combination of the face gear coaxial constant-speed counter-rotating transmission device with four times of power splitting and the dual rotors, which are input by the dual engines of the present invention;
reference numerals: 1. power input shaft, 2, power input cylindrical gear, 3, first class I face gear, 4, second class I face gear, 5, first class II small cylindrical gear, 6, second class II small cylindrical gear, 7, first class II large cylindrical gear, 8, second class II large cylindrical gear, 9, third class II large cylindrical gear, 10, fourth class II large cylindrical gear, 11, first class III small cylindrical gear, 12, second class III small cylindrical gear, 13, third class III small cylindrical gear, 14, fourth class III small cylindrical gear, 15, first class III large cylindrical gear, 16, second class III large cylindrical gear, 17, third class III large cylindrical gear, 18, fourth class III large cylindrical gear, 19, fifth class III large cylindrical gear, 20, sixth class III large cylindrical gear, 21, seventh class III large cylindrical gear, 22, eighth class III large cylindrical gear, 23, The upper gear 24, the lower gear 25, the thrust bearing 26, the upper output shaft 27, the lower output shaft 28, the upper tail wing cylindrical gear 29, the lower tail wing cylindrical gear 30, the upper rotary wing 31 and the lower rotary wing.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The first embodiment is as follows: the embodiment is a single engine input face gear coaxial dual rotor transmission with four power splits, as shown in fig. 1: the device comprises a grading incoming part and a shunting output part;
the grading transmission is a three-level fixed-axis gear train and comprises a level I gear transmission, a level II gear transmission and a level III gear transmission;
the I-stage gear transmission comprises a power input shaft 1, wherein the power input shaft 1 is fixedly connected with a power input cylindrical gear 2 to complete the first-stage transmission of power; the power input cylindrical gear 2 is meshed with the first I-level face gear 3 and the second I-level face gear 4 simultaneously, and radial floating support is adopted to finish primary flow splitting;
the II-stage gear transmission comprises a first II-stage small cylindrical gear 5 and a second II-stage small cylindrical gear 6; the first II-stage small cylindrical gear 5 is fixedly connected with the first I-stage face gear 3 through a torsion dividing shaft, and the second II-stage small cylindrical gear 6 is fixedly connected with the second I-stage face gear 4 through a torsion dividing shaft, so that secondary transmission of power is completed; the first II-stage small cylindrical gear 5 is meshed with the first II-stage large cylindrical gear 7 and the second II-stage large cylindrical gear 8 simultaneously; the second II-stage small cylindrical gear 6 is meshed with the third II-stage large cylindrical gear 9 and the fourth II-stage large cylindrical gear 10 simultaneously, so that secondary flow distribution is completed;
the third-stage gear transmission comprises a first III-stage small cylindrical gear 11, a second III-stage small cylindrical gear 12, a third III-stage small cylindrical gear 13 and a fourth III-stage small cylindrical gear 14, wherein the first III-stage small cylindrical gear 11 is fixedly connected with a first II-stage large cylindrical gear 7 through a double coupling shaft, the second III-stage small cylindrical gear 12 is fixedly connected with a second II-stage large cylindrical gear 8 through a double coupling shaft, the third III-stage small cylindrical gear 13 is fixedly connected with a third II-stage large cylindrical gear 9 through a double coupling shaft, and the fourth III-stage small cylindrical gear 14 is fixedly connected with a fourth II-stage large cylindrical gear 10 through a double coupling shaft to complete three-stage transmission of power; the first III-grade small cylindrical gear 11 is meshed with a first III-grade large cylindrical gear 15 and a second III-grade large cylindrical gear 16 simultaneously; the second III-grade small cylindrical gear 12 is meshed with a third III-grade large cylindrical gear 17 and a fourth III-grade large cylindrical gear 18 simultaneously; the third III-grade small cylindrical gear 13 is meshed with a fifth III-grade large cylindrical gear 19 and a sixth III-grade large cylindrical gear 20 simultaneously; the fourth III-level small cylindrical gear 14 is meshed with the seventh III-level large cylindrical gear 21 and the eighth III-level large cylindrical gear 22 simultaneously, and the three-time flow splitting is completed;
the first III-stage large cylindrical gear 15, the second III-stage large cylindrical gear 16, the fifth III-stage large cylindrical gear 19 and the sixth III-stage large cylindrical gear 20 are simultaneously meshed with an upper gear 23 of the split flow output part; the third III-stage large cylindrical gear 17, the fourth III-stage large cylindrical gear 18, the seventh III-stage large cylindrical gear 21 and the eighth III-stage large cylindrical gear 21 are simultaneously meshed with a lower gear 24 of the split-flow output part, so that power confluence transmission is completed;
the upper gear 23 and the lower gear 24 are supported by a thrust bearing 25 to realize a coaxial contra-rotating function, the upper gear 23 is fixedly connected with an upper output shaft 26, the lower gear 24 is fixedly connected with a lower output shaft 27 to realize reverse double output of power and provide rising power for the system, the upper gear 23 is meshed with an upper tail wing cylindrical gear 28, the lower gear 24 is meshed with a lower tail wing cylindrical gear 29 to complete tail transmission of the power and form propulsion power of the system.
The upper output shaft 26 is a hollow shaft, and the aperture of the upper output shaft is larger than the axial diameter of the lower output shaft 27; the lower output shaft 27 is a hollow shaft, passes through the center of the upper output shaft 26, and is higher than the upper output shaft 26. The upper output shaft 26 is fixedly connected with the lower rotor wing, and the lower output shaft 27 is fixedly connected with the upper rotor wing, so that coaxial contrarotation of the double rotor wings is completed.
Example two:
the embodiment is a dual-engine input face gear coaxial dual-rotor transmission with four power splits, as shown in fig. 2-3: the structure of the power split device is the same as that of the embodiment, and the structure is different from that of the embodiment in that double-engine power input is adopted, namely, the power split device is provided with two power split incoming parts, the two power split incoming parts have the same configuration and are symmetrically or approximately symmetrically distributed along the circumference.
The utility model discloses increase the combined mechanism of two rotors on the basis of the two-way input of embodiment, increased the lower rotor 31 of being connected with last output shaft 26 and the last rotor 30 of being connected with lower output shaft 27, all the other structures are the same with the embodiment, as shown in FIG. 4.
The utility model discloses have quartic power and divide and converge, mainly include the cubic power reposition of redundant personnel transmission of tertiary ordinary gear train to and turn round the primary power that gear wheel and last lower gear meshing accomplished and converge by the tertiary. The mechanism simultaneously forms three paths of power output, including the power output transmitted to the upper rotor wing by the upper gear, the power output transmitted to the upper rotor wing by the lower gear, and the power output transmitted to the tail rotor by the tail gear, thereby forming a lift system and a thrust system of the helicopter.
The above is only the preferred embodiment of the present invention, and is not used to limit the protection scope of the present invention, it should be noted that, without departing from the principles of the present invention, the ordinary skilled person in the art can perform a plurality of improvements and decorations thereon, all should be regarded as the protection scope of the present invention.
Claims (5)
1. The utility model provides a face gear coaxial type dual rotor drive mechanism with quartic power split which characterized in that: comprises a hierarchical input part and an output part; the grading input part comprises a three-level fixed-axis gear train consisting of I-level gear transmission, II-level gear transmission and III-level gear transmission;
the I-stage gear transmission comprises a power input gear and two I-stage face gears, and the power input gear is meshed with the two I-stage face gears to realize first-stage transmission;
the II-stage gear transmission comprises two II-stage small cylindrical gears and four II-stage large cylindrical gears; each II-stage small cylindrical gear is coaxial with one I-stage face gear and is simultaneously meshed with two II-stage large cylindrical gears to realize secondary transmission;
the III-level gear transmission comprises four III-level small cylindrical gears and eight III-level large cylindrical gears, each III-level small cylindrical gear is coaxial with one II-level large cylindrical gear and is meshed with two III-level large cylindrical gears simultaneously, and three-level transmission is realized;
the output part comprises back-to-back upper and lower gears; the upper gear is meshed with four III-level large cylindrical gears and is fixedly connected with an upper output shaft; and the lower gear is meshed with the remaining four III-level large cylindrical gears and is fixedly connected with the lower output shaft to finish power output.
2. A face gear coaxial dual rotor transmission with four power splits according to claim 1 wherein: the upper gear is also meshed with the upper tail wing cylindrical gear, and the lower gear is also meshed with the lower tail wing cylindrical gear.
3. A face gear coaxial dual rotor transmission with four power splits according to claim 1 or 2, characterized in that: and a thrust bearing is arranged between the upper gear and the lower gear.
4. A face gear coaxial dual rotor transmission with four power splits according to claim 3 wherein: the upper output shaft and the lower output shaft are hollow shafts, the lower output shaft penetrates through the center of the upper output shaft and is higher than the upper output shaft, and the rotation directions of the upper output shaft and the lower output shaft are opposite and constant.
5. A face gear coaxial dual rotor transmission with four power splits according to claim 4 wherein: the number of the grading input parts is at least 1, and when multi-path input is adopted, each path has the same configuration and is uniformly arranged along the circumference.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020221906.7U CN211943722U (en) | 2020-02-27 | 2020-02-27 | Face gear coaxial type dual-rotor transmission mechanism with quartic power splitting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020221906.7U CN211943722U (en) | 2020-02-27 | 2020-02-27 | Face gear coaxial type dual-rotor transmission mechanism with quartic power splitting |
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| Publication Number | Publication Date |
|---|---|
| CN211943722U true CN211943722U (en) | 2020-11-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020221906.7U Expired - Fee Related CN211943722U (en) | 2020-02-27 | 2020-02-27 | Face gear coaxial type dual-rotor transmission mechanism with quartic power splitting |
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| CN (1) | CN211943722U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268116A (en) * | 2020-02-27 | 2020-06-12 | 西安工业大学 | Face gear coaxial contra-rotating dual-rotor transmission mechanism |
| CN116384014A (en) * | 2023-06-05 | 2023-07-04 | 中国空气动力研究与发展中心空天技术研究所 | Design method and mechanism of single-rotor adjacent blade reverse constant-speed rotation transmission mechanism |
-
2020
- 2020-02-27 CN CN202020221906.7U patent/CN211943722U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268116A (en) * | 2020-02-27 | 2020-06-12 | 西安工业大学 | Face gear coaxial contra-rotating dual-rotor transmission mechanism |
| CN111268116B (en) * | 2020-02-27 | 2024-03-05 | 西安工业大学 | Face gear coaxial counter-rotating double-rotor transmission mechanism |
| CN116384014A (en) * | 2023-06-05 | 2023-07-04 | 中国空气动力研究与发展中心空天技术研究所 | Design method and mechanism of single-rotor adjacent blade reverse constant-speed rotation transmission mechanism |
| CN116384014B (en) * | 2023-06-05 | 2023-08-18 | 中国空气动力研究与发展中心空天技术研究所 | Design method and mechanism of single-rotor adjacent blade reverse constant-speed rotation transmission mechanism |
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Granted publication date: 20201117 |