CN115432181B - Tilt gyroplane transmission system with input shaft coaxial with rotor shaft - Google Patents
Tilt gyroplane transmission system with input shaft coaxial with rotor shaft Download PDFInfo
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- CN115432181B CN115432181B CN202211229488.6A CN202211229488A CN115432181B CN 115432181 B CN115432181 B CN 115432181B CN 202211229488 A CN202211229488 A CN 202211229488A CN 115432181 B CN115432181 B CN 115432181B
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 80
- 230000009467 reduction Effects 0.000 claims abstract description 110
- 230000007246 mechanism Effects 0.000 claims description 46
- 238000010276 construction Methods 0.000 claims 2
- 238000001816 cooling Methods 0.000 abstract description 3
- 238000010248 power generation Methods 0.000 abstract description 3
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- 238000012986 modification Methods 0.000 description 1
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Abstract
The invention relates to a transmission system of a tilting gyroplane, wherein an input shaft and a rotor shaft are coaxial, the transmission system comprises a middle speed reduction unit, a pair of left rotor wing tilting speed reduction units and right rotor wing tilting speed reduction units which are connected with the middle speed reduction unit through two parallel shafts and have the same structure, and a pair of tilting units connected with the left rotor wing tilting speed reduction units and the right rotor wing tilting speed reduction units; the transmission system adopts left and right engine output, the first-stage bevel gear and the second-stage cylindrical gear in the rotor tilting and decelerating unit are used for decelerating and splitting, and then the power is transmitted to the rotor after being converged through the third-stage bevel gear, so that the coaxial input shaft and the rotor shaft are realized; the residual power is transmitted to the intermediate speed reduction unit to realize power generation, oil supply and cooling of the transmission system; the design that the input shaft is coaxial with the rotor shaft can greatly reduce the weight of a transmission system of the tiltrotor aircraft and reduce the structural size.
Description
Technical Field
The invention belongs to the technical field of aerospace, and relates to a tilting gyroplane transmission system with an input shaft coaxial with a rotor shaft.
Background
In the aerospace field, a conventional helicopter can efficiently hover and vertically take off and land, but the flying speed is low; fixed wing aircraft can fly quickly over long distances under good payloads, but take off over longer distances. The tiltrotor aircraft can combine the advantages of the two types, and can hover and vertically take off and land and fly at a higher speed. The transmission system is one of key moving parts of the tiltrotor, and the main function of the transmission system is to reduce and turn the output power of an engine through a specific transmission ratio and then transmit the output power to left and right rotors and other devices, so that the transmission system is an important power transmission system of the tiltrotor. The transmission system of tiltrotor aircraft must be more compact, lighter, and more reliable, while meeting the requirements for tiltrotor rotation and tilt functions. Because the speed ratio of the transmission system of the tiltrotor aircraft is very large, the non-coaxial transmission system of the tiltrotor aircraft at home and abroad at present mostly meets the speed ratio requirement by arranging a multi-stage intermediate speed reduction unit, so that the weight of the whole transmission system is large, and the structural size is large. There is therefore a need for a tiltrotor aircraft transmission system in which the engine input shaft is coaxial with the rotor shaft to avoid the problems associated with the designs described above.
Disclosure of Invention
In view of this, the invention provides a tilting rotorcraft transmission system with light weight, compact structure, high transmission efficiency and more stable input shaft and rotor shaft coaxial in order to solve the problems that the whole transmission system has large weight and large structural size and affects the application range of the existing non-coaxial tilting rotorcraft transmission system in order to meet the speed ratio requirement required by design.
In order to achieve the above purpose, the present invention provides the following technical solutions:
The transmission system of the tiltrotor aircraft with the input shaft coaxial with the rotor shaft comprises a middle speed reduction unit, a pair of left rotor wing tilting speed reduction units and right rotor wing tilting speed reduction units, wherein the left rotor wing tilting speed reduction units and the right rotor wing tilting speed reduction units are symmetrically connected to the middle speed reduction unit through two parallel axles, and the pair of tilting units are connected to the left rotor wing tilting speed reduction units and the right rotor wing tilting speed reduction units;
The rotor tilting speed reduction unit comprises an engine input shaft, a transmission shaft in transmission connection with the engine input shaft, a tilting shaft in transmission connection with the transmission shaft, an output shaft in transmission connection with the tilting shaft, a rotor shaft in transmission connection with the output shaft, a first-stage reversing speed reduction input bevel gear, a first-stage reversing speed reduction output bevel gear meshed with the first-stage reversing speed reduction input bevel gear, a second-stage speed reduction input cylindrical gear, a second-stage speed reduction output cylindrical gear meshed with the second-stage speed reduction input cylindrical gear, a third-stage reversing input bevel gear, a third-stage reversing output bevel gear meshed with the third-stage reversing input bevel gear, a fourth-stage speed reduction planetary gear and a fifth-stage speed reduction planetary gear connected with a planetary frame of the fourth-stage speed reduction planetary gear; the transmission shafts positioned on the left side and the right side of the input shaft of the engine are respectively provided with a first-stage reversing speed reduction output bevel gear and a second-stage speed reduction input cylindrical gear; a second-stage reduction output cylindrical gear and a third-stage reversing input bevel gear are arranged on the tilting shaft; a fourth-stage reduction planetary gear is arranged on the third-stage reversing output bevel gear; a fifth-stage speed reduction planetary gear is arranged on the rotor shaft;
the middle speed reducing unit comprises a braking input shaft, a middle shaft fixedly connected with the parallel shaft, an alternating current motor input shaft, a direct current motor input shaft, an oil pump input shaft, a hydraulic pump input shaft, a fan input shaft, a braking mechanism gear, an alternating current motor gear, a direct current motor gear, an oil pump mechanism gear, a hydraulic pump mechanism gear and a fan gear; the intermediate shaft is provided with a first cylindrical gear and a second cylindrical gear, a brake mechanism gear arranged on the brake input shaft is meshed with the first cylindrical gear, an alternating current motor gear arranged on the alternating current motor input shaft is meshed with the second cylindrical gear, and the alternating current motor gear is meshed with a direct current motor gear arranged on the direct current motor input shaft; a third cylindrical gear is further arranged on the direct current motor input shaft and meshed with an oil pump mechanism gear arranged on the oil pump input shaft, and a hydraulic pump mechanism gear arranged on the hydraulic pump input shaft is meshed with the oil pump mechanism gear; a fourth cylindrical gear is also arranged on the hydraulic pump input shaft and meshed with a fan gear arranged on the fan input shaft;
Each tilting unit comprises a frame, a tilting mechanism and a tilting bracket outside a fourth-stage reduction planetary gear in the rotor tilting and decelerating unit, and tilting is realized by hydraulically driving a tilting shaft.
Further, in the rotor tilting speed reducing unit, an input shaft of the engine and a first-stage reversing speed reducing input bevel gear are of an integrated structure, and an output shaft and a third-stage reversing output bevel gear are of an integrated structure.
Further, in the rotor tilting speed reduction unit, an engine input shaft is provided with face-to-face mounted angular contact ball bearings to provide support, and a transmission shaft and a tilting shaft are provided with cylindrical roller bearings and face-to-face mounted angular contact ball bearings to provide support; face-to-face mounted angular contact ball bearings are mounted on the output shaft to provide support, and back-to-back tapered roller bearings are mounted on the rotor shaft to provide support.
Further, a transmission shaft in the rotor tilting speed reducing unit is in spline connection with a first-stage reversing speed reducing output bevel gear and is in spline connection with a second-stage speed reducing input cylindrical gear; the tilting shaft is in spline connection with a third-stage reversing input bevel gear and in spline connection with a second-stage decelerating output cylindrical gear; the output shaft is in spline connection with the fourth-stage reduction planetary gear; the rotor shaft is in spline connection with the fifth-stage reduction planetary gear.
Further, face-to-face mounted angular contact ball bearings are mounted on the brake input shaft, the intermediate shaft, the ac motor input shaft, the dc motor input shaft, the oil pump input shaft, the hydraulic pump input shaft, and the fan input shaft in the intermediate reduction unit to provide support.
Further, in the intermediate reduction unit, a brake input shaft, an intermediate shaft, an alternating current motor input shaft, a direct current motor input shaft, an oil pump input shaft, a hydraulic pump input shaft, a fan input shaft are in spline connection with a brake mechanism gear, an alternating current motor gear, a direct current motor gear, an oil pump mechanism gear, a hydraulic pump mechanism gear, a fan gear, a first cylindrical gear, a second cylindrical gear, a third cylindrical gear and a fourth cylindrical gear.
Further, each tilting unit comprises a frame, a tilting mechanism and a tilting bracket outside a fourth-stage reduction planetary gear in the rotor tilting reduction unit, one end of each of two sides of the tilting mechanism is connected with the frame, one end of each of two sides of the tilting mechanism is connected with the outside of the fourth-stage reduction planetary gear in the rotor reduction unit, and tilting is realized around a tilting shaft through hydraulic driving.
Further, angular contact ball bearings are mounted on the two side axles to provide support.
The invention has the beneficial effects that:
1. The invention discloses a transmission system of a tilting gyroplane with an input shaft coaxial with a rotor shaft, which adopts left and right engine output, reduces speed and divides flow through a first-stage bevel gear and a second-stage cylindrical gear in a rotor tilting speed reduction unit, and then transmits power to left and right rotors after converging through a third-stage bevel gear, so that the coaxial of the input shaft and the rotor shaft is realized; compared with the traditional tilting wing transmission system, the structure is more compact, the weight of the system can be greatly reduced, and the structural size is reduced.
2. According to the tilting rotorcraft transmission system with the input shaft coaxial with the rotor shaft, the residual power is transmitted to the intermediate speed reduction unit to realize power generation, oil supply and cooling of the transmission system, and the energy utilization efficiency is improved.
3. The invention discloses a transmission system of a tilting gyroplane with an input shaft coaxial with a rotor shaft, which adopts a two-stage bevel gear pair, a two-stage planetary gear train and a one-stage cylindrical gear pair; the bevel gear pair is used for decelerating and reversing, the planetary gear train and the cylindrical gear pair are used for decelerating, the structure is compact, and the transmission efficiency is high.
4. According to the transmission system of the tilting rotorcraft with the input shaft coaxial with the rotor shaft, the input shaft output shaft and the first-stage speed reduction reversing input bevel gear and the third-stage reversing output bevel gear in the rotor tilting speed reduction unit are of an integrated structure, and the input shaft, the transmission shaft, the tilting shaft and the output shaft are provided with face-to-face installed angular contact ball bearings, so that axial force generated by meshing of the transmission system can be counteracted; the cylindrical gear, the planetary gear train, the first-stage speed reduction reversing output bevel gear and the third-stage reversing input bevel gear are connected through splines, so that the dislocation rate is reduced, and the stability of a transmission system is improved.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention. The objects and other advantages of the invention may be realized and obtained by means of the instrumentalities and combinations particularly pointed out in the specification.
Drawings
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in the following preferred detail with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of a tiltrotor aircraft transmission system having an input shaft coaxial with a rotor shaft in accordance with the present invention;
figure 2 is a front view of the tiltrotor aircraft transmission system with the input shaft coaxial with the rotor shaft of the present invention;
figure 3 is a transmission schematic of the tiltrotor aircraft transmission system with the input shaft coaxial with the rotor shaft of the present invention.
Reference numerals: the engine input shaft 1, the first-stage reversing reduction gear 4, the first-stage reversing reduction gear 5, the transmission shaft 8, the second-stage reversing reduction gear 11, the second-stage reversing gear 12, the tilting shaft 13, the third-stage reversing gear 18, the third-stage reversing gear 19, the output shaft 22, the fourth-stage reversing planetary gear 23, the fifth-stage reversing planetary gear 24, the rotor shaft 25, and the axle 32, the brake mechanism gear 34, the brake input shaft 35, the first-stage reversing gear 37, the second-stage reversing gear 38, the intermediate shaft 39, the alternating current motor gear 42, the alternating current motor input shaft 43, the direct current motor gear 46, the third-stage reversing gear 48, the direct current motor input shaft 49, the oil pump mechanism gear 51, the oil pump input shaft 53, the fourth reversing gear 56, the hydraulic pump input shaft 57, the hydraulic pump mechanism gear 58, the fan input shaft 61, the fan gear 62, the tilting mechanism 64, the angular contact ball bearings 2,3, 6, 7, 16, 17, 20, 21, 28, 29, 30, 31, 33, 36, 40, 41, 44, 45, 47, 50, 52, 54, 55, 60, 9, 14, 15, and 15.
Detailed Description
Other advantages and effects of the present invention will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present invention with reference to specific examples. The invention may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present invention. It should be noted that the illustrations provided in the following embodiments merely illustrate the basic idea of the present invention by way of illustration, and the following embodiments and features in the embodiments may be combined with each other without conflict.
Wherein the drawings are for illustrative purposes only and are shown in schematic, non-physical, and not intended to limit the invention; for the purpose of better illustrating embodiments of the invention, certain elements of the drawings may be omitted, enlarged or reduced and are not representative of actual product dimensions; it will be appreciated by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.
The same or similar reference numbers in the drawings of embodiments of the invention correspond to the same or similar components; in the description of the present invention, it should be understood that, if there are terms such as "upper", "lower", "left", "right", "front", "rear", etc., that indicate an azimuth or a positional relationship based on the azimuth or the positional relationship shown in the drawings, it is only for convenience of describing the present invention and simplifying the description, but not for indicating or suggesting that the referred device or element must have a specific azimuth, be constructed and operated in a specific azimuth, so that the terms describing the positional relationship in the drawings are merely for exemplary illustration and should not be construed as limiting the present invention, and that the specific meaning of the above terms may be understood by those of ordinary skill in the art according to the specific circumstances.
The tiltrotor aircraft transmission system with the input shaft coaxial with the rotor shaft as shown in fig. 1 to 3 includes a central speed reduction unit, a pair of right and left rotor tilting speed reduction units of identical structure symmetrically connected to the central speed reduction unit through two parallel axles 32, and a pair of tilting units connected to the right and left rotor tilting speed reduction units.
The rotor tilting speed reduction unit comprises an engine input shaft 1, a left transmission shaft and a right transmission shaft 8 which are in transmission connection with the engine input shaft 1, a tilting shaft 13 which is in transmission connection with the transmission shaft 8, an output shaft 22 which is in transmission connection with the tilting shaft 13, a rotor shaft 25 which is in transmission connection with the output shaft 22, a first-stage reversing speed reduction input bevel gear 4, a first-stage reversing speed reduction output bevel gear 5 which is meshed with the first-stage reversing speed reduction input bevel gear 4, a second-stage speed reduction input cylindrical gear 11, a second-stage speed reduction output cylindrical gear 12 which is meshed with the second-stage speed reduction input cylindrical gear 11, a third-stage reversing input bevel gear 18, a third-stage reversing output bevel gear 19 which is meshed with the third-stage reversing input bevel gear 18, a fourth-stage speed reduction planetary gear 23 and a fifth-stage speed reduction planetary gear 24 which is meshed with the fourth-stage speed reduction planetary gear 23;
The engine input shaft 1 and the first-stage reversing and decelerating bevel gear 4 are of an integrated structure, a first-stage reversing and decelerating bevel gear 5 and a second-stage decelerating and entering cylindrical gear 11 are arranged on transmission shafts 8 positioned on the left side and the right side of the engine input shaft 1, and power is split and transmitted to the transmission shafts 8 on the left side and the right side of the engine input shaft 1 through the cooperation of the first-stage reversing and decelerating bevel gear 4 and the first-stage reversing and decelerating bevel gear 5;
The tilting shaft 13 is provided with a second-stage reduction gear 12 and a third-stage reversing bevel gear 18, and the power on the transmission shaft 8 is transmitted to the tilting shaft 13 through the second-stage reduction gear 11 and the second-stage reduction gear 12; the output shaft 22 and the third-stage reversing output bevel gear 19 are of an integrated structure, a fourth-stage reduction planetary gear 23 is arranged on the output shaft, and the power of the tilting shaft 13 can be converged and transmitted to the output shaft 22 through the third-stage reversing input bevel gear 18 and the third-stage reversing output bevel gear 19; the fifth-stage reduction planetary gear 24 is mounted on the rotor shaft 25, and the power of the output shaft 22 is transmitted to the left and right rotors through the fourth-stage reduction planetary gear 23 and the fifth-stage reduction planetary gear 24.
The engine input shaft 1 is provided with face-to-face mounted angular contact ball bearings 2, 3 to provide support. Cylindrical roller bearings 9,10, 14, 15 and face-to-face mounted angular contact ball bearings 6, 7, 16, 17 are mounted on the drive shaft 8 and the tilting shaft 13 to provide support. Face-to-face mounted angular contact ball bearings 20, 21 are mounted on the output shaft 22 to provide support. Back-to-back tapered roller bearings 26, 27 are mounted on rotor shaft 25 to provide support. The transmission shaft 8 is in spline connection with the first-stage reversing speed reduction output bevel gear 5 and in spline connection with the second-stage speed reduction input cylindrical gear 11. The tilting shaft 13 is in spline connection with a third-stage reversing bevel gear 18 and in spline connection with a second-stage decelerating spur gear 12. The output shaft 22 is spline-connected with the fourth-stage reduction planetary gear 23. The rotor shaft 25 is splined to the fifth stage reduction planets 24.
The intermediate reduction unit includes a brake input shaft 35, an intermediate shaft 39 fixedly connected to the parallel shaft 32, an ac motor input shaft 43, a dc motor input shaft 49, an oil pump input shaft 53, a hydraulic pump input shaft 57, a fan input shaft 61, a brake mechanism gear 34, an ac motor gear 42, a dc motor gear 46, an oil pump mechanism gear 51, a hydraulic pump mechanism gear 58, and a fan gear 62;
The intermediate shaft 39 is provided with a first cylindrical gear 37 and a second cylindrical gear 38, the brake mechanism gear 34 arranged on the brake input shaft 35 is meshed with the first cylindrical gear 37, the alternating current motor gear 42 arranged on the alternating current motor input shaft 43 is meshed with the second cylindrical gear 38, and the alternating current motor gear 42 is meshed with the direct current motor gear 46 arranged on the direct current motor input shaft 49; the dc motor input shaft 49 is further provided with a third spur gear 48, the third spur gear 48 is meshed with an oil pump mechanism gear 51 provided on an oil pump input shaft 53, and a hydraulic pump mechanism gear 58 provided on a hydraulic pump input shaft 57 is meshed with the oil pump mechanism gear 51; the hydraulic pump input shaft 57 is also provided with a fourth spur gear 56, and the fourth spur gear 56 is meshed with a fan gear 62 mounted on a fan input shaft 61.
The brake input shaft 35, the intermediate shaft 39, the ac motor input shaft 43, the dc motor input shaft 49, the oil pump input shaft 53, the hydraulic pump input shaft 57, and the fan input shaft 61 are mounted with angular ball bearings 33, 36, 40, 41, 44, 45, 47, 50, 52, 54, 55, 59, 60, 63 to provide support. The brake input shaft 35, the intermediate shaft 39, the ac motor input shaft 43, the dc motor input shaft 49, the oil pump input shaft 53, the hydraulic pump input shaft 57, and the fan input shaft 61 are spline-connected to the brake mechanism gear 34, the ac motor gear 42, the dc motor gear 46, the oil pump mechanism gear 51, the hydraulic pump mechanism gear 58, the fan gear 62, the first spur gear 37, the second spur gear 38, the third spur gear 48, and the fourth spur gear 56.
The two parallel axles 32 on both sides of the intermediate speed reduction unit are provided, and the angular ball bearings 28, 29, 30, 31 are mounted on the parallel axles 32 to provide support.
Each tilting unit comprises a frame, a tilting mechanism 64 and a tilting bracket outside the fourth-stage reduction planetary gear 23 in the rotor tilting speed reduction unit, and tilting is realized around a tilting shaft through hydraulic driving.
The transmission system of the tiltrotor with the input shaft coaxial with the rotor shaft consists of a rotor tilting speed reduction unit and an intermediate speed reduction unit. The power (left side) is input by the engine input shaft 1, is shunted to the left and right transmission shafts 8 through the first-stage reversing and decelerating bevel gears 4 and the first-stage reversing and decelerating bevel gears 5, the transmission shafts 8 transmit the power to the tilting shafts 13 through the second-stage reversing and decelerating cylindrical gears 11 and the second-stage decelerating and decelerating cylindrical gears 12, the first tilting shafts transmit the power to the output shafts 22 through the third-stage reversing and decelerating bevel gears 18 and the third-stage reversing and decelerating bevel gears 19, and the output shafts 22 transmit the power to the rotor wings through the fourth-stage decelerating planetary gears 23 and the fifth-stage decelerating planetary gears 24. The right transfer route is the same as the left transfer route. The remaining power is transferred by the parallel axles 32 to the intermediate reduction unit for power generation, oil supply and cooling of the drive train. The brake mechanism gear 34 is engaged with a first spur gear 37 mounted on an intermediate shaft 39 to effect braking of the transmission.
When the transmission system of the tiltrotor with the coaxial input shaft and the rotor shaft works, power is input by the engine input shaft 1, the engine input shaft 1 drives the first-stage reversing and decelerating input bevel gear 4 and the first-stage reversing and decelerating output bevel gear 5 to rotate, the transmission shaft 8 is in spline connection with the first-stage reversing and decelerating output bevel gear 5 and is in spline connection with the second-stage decelerating input cylindrical gear 11, the tilting shaft 13 is in spline connection with the third-stage reversing and input bevel gear 18 and the second-stage decelerating output cylindrical gear 12, the second-stage decelerating input cylindrical gear 11 and the second-stage decelerating output cylindrical gear 12 drive the tilting shaft 13 to rotate, the output shaft 22 and the third-stage reversing and decelerating output bevel gear 19 are in integral structure and are in spline connection with the fourth-stage decelerating planetary gear 23, the third-stage reversing and decelerating output bevel gear 19 drive the output shaft 22 to rotate, and the rotor shaft is in spline connection with the fifth-stage decelerating planetary gear 24, and the fourth-stage decelerating planetary gear 23 and the fifth-stage decelerating planetary gear 24 drive the rotor shaft to rotate, and power is output.
When tilting, a hydraulic device (not shown) is connected with the tilting mechanism 64, and transmits power to the tilting mechanism 64, and the tilting mechanism 64 drives the rotors on the left side and the right side to tilt within a certain range.
Finally, it is noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the spirit and scope of the present invention, which is intended to be covered by the claims of the present invention.
Claims (8)
1. The transmission system of the tiltrotor aircraft with the input shaft coaxial with the rotor shaft is characterized by comprising a middle speed reduction unit, a pair of left and right rotor tilting speed reduction units with the same structure and connected with the middle speed reduction unit in a parallel-axis symmetrical manner, and a pair of tilting units connected with the left and right rotor tilting speed reduction units;
The rotor tilting speed reduction unit comprises an engine input shaft, a transmission shaft in transmission connection with the engine input shaft, a tilting shaft in transmission connection with the transmission shaft, an output shaft in transmission connection with the tilting shaft, a rotor shaft in transmission connection with the output shaft, a first-stage reversing speed reduction input bevel gear, a first-stage reversing speed reduction output bevel gear meshed with the first-stage reversing speed reduction input bevel gear, a second-stage speed reduction input cylindrical gear, a second-stage speed reduction output cylindrical gear meshed with the second-stage speed reduction input cylindrical gear, a third-stage reversing input bevel gear, a third-stage reversing output bevel gear meshed with the third-stage reversing input bevel gear, a fourth-stage speed reduction planetary gear and a fifth-stage speed reduction planetary gear connected with a planetary frame of the fourth-stage speed reduction planetary gear; the transmission shafts positioned on the left side and the right side of the input shaft of the engine are respectively provided with a first-stage reversing speed reduction output bevel gear and a second-stage speed reduction input cylindrical gear; a second-stage reduction output cylindrical gear and a third-stage reversing input bevel gear are arranged on the tilting shaft; a fourth-stage reduction planetary gear is arranged on the third-stage reversing output bevel gear; a fifth-stage speed reduction planetary gear is arranged on the rotor shaft;
the middle speed reducing unit comprises a braking input shaft, a middle shaft fixedly connected with the parallel shaft, an alternating current motor input shaft, a direct current motor input shaft, an oil pump input shaft, a hydraulic pump input shaft, a fan input shaft, a braking mechanism gear, an alternating current motor gear, a direct current motor gear, an oil pump mechanism gear, a hydraulic pump mechanism gear and a fan gear; the intermediate shaft is provided with a first cylindrical gear and a second cylindrical gear, a brake mechanism gear arranged on the brake input shaft is meshed with the first cylindrical gear, an alternating current motor gear arranged on the alternating current motor input shaft is meshed with the second cylindrical gear, and the alternating current motor gear is meshed with a direct current motor gear arranged on the direct current motor input shaft; a third cylindrical gear is further arranged on the direct current motor input shaft and meshed with an oil pump mechanism gear arranged on the oil pump input shaft, and a hydraulic pump mechanism gear arranged on the hydraulic pump input shaft is meshed with the oil pump mechanism gear; a fourth cylindrical gear is also arranged on the hydraulic pump input shaft and meshed with a fan gear arranged on the fan input shaft;
Each tilting unit comprises a frame, a tilting mechanism and a tilting bracket outside a fourth-stage reduction planetary gear in the rotor tilting and decelerating unit, and tilting is realized by hydraulically driving a tilting shaft.
2. The tiltrotor aircraft transmission system according to claim 1, wherein the input shaft of the engine in the rotor tiltrotor reduction unit is of unitary construction with the first-stage reversing reduction entry bevel gear and the output shaft is of unitary construction with the third-stage reversing exit bevel gear.
3. The tiltrotor aircraft transmission system according to claim 2, wherein the rotor tiltrotor speed reduction unit has an engine input shaft with face-to-face mounted angular contact ball bearings to provide support, and the drive shaft and tiltrotor shaft have cylindrical roller bearings and face-to-face mounted angular contact ball bearings mounted thereon to provide support; face-to-face mounted angular contact ball bearings are mounted on the output shaft to provide support, and back-to-back tapered roller bearings are mounted on the rotor shaft to provide support.
4. The tiltrotor aircraft transmission system of claim 3, wherein the drive shaft in the rotor tilter unit is in splined connection with a first stage reversing and decelerating out-bevel gear and in splined connection with a second stage decelerating in-spur gear; the tilting shaft is in spline connection with a third-stage reversing input bevel gear and in spline connection with a second-stage decelerating output cylindrical gear; the output shaft is in spline connection with the fourth-stage reduction planetary gear; the rotor shaft is in spline connection with the fifth-stage reduction planetary gear.
5. The tiltrotor aircraft transmission system according to claim 1, wherein face-to-face mounted angular contact ball bearings are mounted on the brake input shaft, intermediate shaft, ac motor input shaft, dc motor input shaft, oil pump input shaft, hydraulic pump input shaft, fan input shaft in the intermediate reduction unit to provide support.
6. The tiltrotor aircraft transmission system according to claim 5, wherein the brake input shaft, the intermediate shaft, the ac motor input shaft, the dc motor input shaft, the oil pump input shaft, the hydraulic pump input shaft, the fan input shaft are splined to the brake mechanism gear, the ac motor gear, the dc motor gear, the oil pump mechanism gear, the hydraulic pump mechanism gear and the fan gear, the first spur gear, the second spur gear, the third spur gear, and the fourth spur gear in the intermediate reduction unit.
7. The tiltrotor aircraft transmission system of claim 1, wherein each tilter unit comprises a frame, a tilter mechanism, and a tilting bracket outside a fourth-stage reduction planetary gear in the rotor tilting and decelerating unit, wherein one end of each of two sides of the tilter mechanism is connected to the frame, and one end is connected to the outside of the fourth-stage reduction planetary gear in the rotor tilting and decelerating unit, and tilting is achieved by hydraulically driving the tilting shaft.
8. The tiltrotor aircraft transmission system according to claim 1, wherein the two-sided parallel axles are mounted with angular contact ball bearings to provide support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211229488.6A CN115432181B (en) | 2022-10-08 | Tilt gyroplane transmission system with input shaft coaxial with rotor shaft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211229488.6A CN115432181B (en) | 2022-10-08 | Tilt gyroplane transmission system with input shaft coaxial with rotor shaft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115432181A CN115432181A (en) | 2022-12-06 |
| CN115432181B true CN115432181B (en) | 2024-04-19 |
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