阅读说明：本技术 一种用于共轴直升机主减速器的分扭齿轮传动减速装置 (Torque-dividing gear transmission speed reducer for main speed reducer of coaxial helicopter ) 是由 胡明辉 曾利 陈广艳 张镇宇 于 2021-07-07 设计创作，主要内容包括：本发明属于直升机主减速器传动领域,涉及一种用于共轴直升机主减速器的分扭齿轮传动减速装置；本发明的发动机输出轴通过超越离合器与动力输入轴相连接,动力输入轴上固定有两个主动锥齿轮,分别与两个从动锥齿轮啮合,从而实现换向,分扭,并且两个从动锥齿轮的小端端面相对布置,从而使得两个旋翼轴的转向相反,本发明用于共轴直升机的分扭传动减速装置,在第一级减速采用锥齿轮分扭,在第二级减速采用圆柱齿轮分扭传动,功率经过多支路分流,各支路中齿轮所传递的扭矩降低,使得采用的齿轮齿数较少、体积较小、质量轻、振动噪声小,提高了齿轮的承载能力、疲劳寿命,可以实现大传动比、大功率传动。(The invention belongs to the field of transmission of a helicopter main reducer, and relates to a torque-dividing gear transmission speed reducer for a coaxial helicopter main reducer; the invention relates to a torque-dividing transmission speed reducer for a coaxial helicopter, which is characterized in that an engine output shaft is connected with a power input shaft through an overrunning clutch, two driving bevel gears are fixed on the power input shaft and are respectively meshed with two driven bevel gears so as to realize reversing and torque-dividing, and the small end surfaces of the two driven bevel gears are oppositely arranged so as to ensure that the rotation directions of two rotor shafts are opposite.)

1. A divide and turn round gear drive decelerator for coaxial helicopter main reducer which characterized in that:

the device comprises a first gear shaft, a second gear shaft, a third gear shaft, a fourth gear shaft, a fifth gear shaft, a sixth gear shaft, a first rotor output shaft, a second rotor output shaft and a power input shaft, wherein the first gear shaft, the second gear shaft, the third gear shaft, the fourth gear shaft, the fifth gear shaft, the sixth gear shaft, the first rotor output shaft and the second rotor output shaft are arranged in parallel;

the first gear shaft is provided with a first driven bevel gear and a first torque splitting driving gear; a second torque-dividing driven gear and a first coaxial driving gear are arranged on the second gear shaft; a first torque splitting driven gear and a second coaxial driving gear are arranged on the third gear shaft; a second torque splitting driving gear and a second driven bevel gear are arranged on the fourth gear shaft; a fourth torque output gear and a fourth coaxial driving gear are arranged on the fifth gear shaft; a third torque division driven gear and a third coaxial driving gear are arranged on the sixth gear shaft; a first driving bevel gear and a second driving bevel gear are arranged on the power input shaft;

a second coaxial driven gear is arranged on the first rotor output shaft; a first coaxial driven gear is arranged on the output shaft of the second rotor; the first rotor output shaft is coaxially arranged with the second rotor output shaft;

the first driving bevel gear is meshed with the first driven bevel gear; the second driving bevel gear is meshed with the second driven bevel gear; the first torque splitting driving gear is meshed with the first torque splitting driven gear and the second torque splitting driven gear; the second coaxial driven gear is meshed with the first coaxial driving gear and the second coaxial driving gear; the second torque splitting driving gear is meshed with the third torque splitting driven gear and the fourth torque splitting driven gear; the first coaxial driven gear is in meshing engagement with the third coaxial drive gear and the fourth coaxial drive gear.

2. The torque splitting gear reduction unit for a main reducer of a coaxial helicopter according to claim 1, characterized in that: the second rotor output shaft is disposed through the first rotor output shaft.

3. The torque splitting gear reduction unit for a main reducer of a coaxial helicopter according to claim 1, characterized in that: the first gear shaft is perpendicular to the power input shaft.

4. The torque splitting gear reduction unit for a main reducer of a coaxial helicopter according to claim 1, characterized in that: the output shaft of the engine is connected with the power input shaft through a clutch.

5. The torque splitting gear reduction unit for a main reducer of a coaxial helicopter according to claim 1, characterized in that: the small end face of the first driven bevel gear is arranged opposite to the small end face of the second driven bevel gear.

Technical Field

The invention belongs to the field of transmission of a helicopter main reducer, and relates to a torque-dividing gear transmission speed reducer for a coaxial helicopter main reducer.

Background

The main reducer of the helicopter is used for transmitting the motion and power of an engine to a rotor wing, a tail reducer and accessories according to a certain proportion, and is an essential transmission component for power output of the engine. As one of three large moving parts of the helicopter, the transmission performance of the helicopter directly influences the running performance, the safety performance and the reliability of the helicopter. The coaxial helicopter is a development hotspot of future helicopters at present; the main reducer of the coaxial helicopter is provided with two rotor output shafts which have opposite steering and torque, equal torque and coincident axes, and the structure of the main reducer is special and complex. It is therefore necessary to design the final drive of a coaxial helicopter exclusively.

In order to reduce the load of the gear, a gear shunting structure is widely applied to a main reducer structure of the helicopter, and a planetary gear train and a face gear shunting structure are common shunting structures.

The Ka28 helicopter main reducer designed by Carmoff's design office adopts a closed differential gear train to carry out power output, and the closed differential planetary gear train is based on a differential gear train and adopts a star-shaped ordinary gear train to close the differential gear train to form a gear train with the degree of freedom of 1, and the sun gear of the star-shaped ordinary gear train is used as input, and two-way output is realized through a planet carrier and an inner gear ring of the differential gear train. However, the output structure is difficult to prepare, has a more complex structure and has high requirements on manufacturing precision and installation.

In addition, in the prior art, face gear torque-splitting transmission is adopted in first-stage gear transmission, so that the load of a next-stage gear is reduced while the power is changed, and two groups of face gears are adopted for one shaft of the stage, so that the power is further split. However, the existing domestic face gear transmission technology has some problems, for example, the bearing capacity of the face gear is limited because the face gear cannot be designed to be too long due to the influence of tooth top sharpening of an undercut.

Disclosure of Invention

In view of the above, the present invention provides a torque-dividing gear transmission speed reducer for a main speed reducer of a coaxial helicopter, which realizes reversing through torque-dividing transmission of a first-stage bevel gear and torque-dividing transmission of a second-stage cylindrical gear.

In order to achieve the purpose, the invention provides the following technical scheme:

a torque-dividing gear transmission speed reducer for a main speed reducer of a coaxial helicopter comprises a first gear shaft, a second gear shaft, a third gear shaft, a fourth gear shaft, a fifth gear shaft, a sixth gear shaft, a first rotor output shaft, a second rotor output shaft and a power input shaft, wherein the first gear shaft, the second gear shaft, the third gear shaft, the fourth gear shaft, the fifth gear shaft, the sixth gear shaft, the first rotor output shaft and the second rotor output shaft are arranged in parallel;

the first gear shaft is provided with a first driven bevel gear and a first torque splitting driving gear; a second torque-dividing driven gear and a first coaxial driving gear are arranged on the second gear shaft; a first torque splitting driven gear and a second coaxial driving gear are arranged on the third gear shaft; a second torque splitting driving gear and a second driven bevel gear are arranged on the fourth gear shaft; a fourth torque output gear and a fourth coaxial driving gear are arranged on the fifth gear shaft; a third torque division driven gear and a third coaxial driving gear are arranged on the sixth gear shaft; a first driving bevel gear and a second driving bevel gear are arranged on the power input shaft;

a second coaxial driven gear is arranged on the first rotor output shaft; a first coaxial driven gear is arranged on the output shaft of the second rotor; the first rotor output shaft is coaxially arranged with the second rotor output shaft;

the first driving bevel gear is meshed with the first driven bevel gear; the second driving bevel gear is meshed with the second driven bevel gear; the first torque splitting driving gear is meshed with the first torque splitting driven gear and the second torque splitting driven gear; the second coaxial driven gear is meshed with the first coaxial driving gear and the second coaxial driving gear; the second torque splitting driving gear is meshed with the third torque splitting driven gear and the fourth torque splitting driven gear; the first coaxial driven gear is in meshing engagement with the third coaxial drive gear and the fourth coaxial drive gear.

Optionally, the second rotor output shaft is disposed through the first rotor output shaft.

Optionally, the first gear shaft is perpendicular to the power input shaft.

Optionally, the engine output shaft is connected to the power input shaft via a clutch.

Optionally, the small end face of the first driven bevel gear is arranged opposite to the small end face of the second driven bevel gear.

The invention has the beneficial effects that:

the torque-dividing transmission speed reducer for the coaxial helicopter adopts bevel gear torque division at the first stage of speed reduction and cylindrical gear torque division transmission at the second stage of speed reduction, power is divided by a plurality of branches, and torque transmitted by gears in each branch is reduced, so that the adopted gears have fewer teeth, smaller volume, light weight and small vibration noise, the bearing capacity and fatigue life of the gears are improved, and large transmission ratio and high-power transmission can be realized.

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 objectives and other advantages of the invention may be realized and attained by the means of the instrumentalities and combinations particularly pointed out hereinafter.

Drawings

For the purposes of promoting a better understanding of the objects, aspects and advantages of the invention, reference will now be made to the following detailed description taken in conjunction with the accompanying drawings in which:

fig. 1 is a schematic view of the overall structure of the present invention.

Reference numerals: 1. the engine comprises an engine output shaft, 2, a clutch, 3, a power input shaft, 4, a first driving bevel gear, 5, a first driven bevel gear, 6, a first gear shaft, 7, a first torque splitting driving gear, 8, a first torque splitting driven gear, 9, a second torque splitting driven gear, 10, a first coaxial driving gear, 11, a second gear shaft, 12, a second coaxial driving gear, 13, a third gear shaft, 14, a second driving bevel gear, 15, a second driven bevel gear, 16, a fourth gear shaft, 17, a third torque splitting driven gear, 18, a second torque splitting driving gear, 19, a fourth torque splitting driven gear, 20, a third coaxial driving gear, 21, a fourth coaxial driving gear, 22, a fifth gear shaft, 23, a sixth gear shaft, 24, a first coaxial driven gear, 25, a second coaxial driven gear, 26, a first rotor output shaft, 27 and a second rotor output shaft.

Detailed Description

The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention in a schematic way, and the features in the following embodiments and examples may be combined with each other without conflict.

Wherein the showings are for the purpose of illustrating the invention only and not for the purpose of limiting the same, and in which there is shown by way of illustration only and not in the drawings in which there is no intention to limit the invention thereto; to better illustrate the embodiments of the present invention, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood 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 numerals in the drawings of the embodiments of the present invention correspond to the same or similar components; in the description of the present invention, it should be understood that if there is an orientation or positional relationship indicated by terms such as "upper", "lower", "left", "right", "front", "rear", etc., based on the orientation or positional relationship shown in the drawings, it is only for convenience of description and simplification of description, but it is not an indication or suggestion that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and therefore, the terms describing the positional relationship in the drawings are only used for illustrative purposes, and are not to be construed as limiting the present invention, and the specific meaning of the terms may be understood by those skilled in the art according to specific situations.

Referring to the drawing, the torque-dividing gear transmission speed reducer for the main speed reducer of the coaxial helicopter is characterized in that an engine output shaft 1 is connected with a power input shaft 3 through a clutch 2, a first driving bevel gear 4 and a second driving bevel gear 14 are fixed on the power input shaft 3, the first driving bevel gear 4 is meshed with a first driven bevel gear 5, and the second driving bevel gear 14 is meshed with a second driven bevel gear 15, so that one-time current dividing, one-time reversing and one-stage speed reducing are realized; the first driven bevel gear 5 and the first torque splitting driving gear 7 are fixed on the first gear shaft 6, and the first torque splitting driving gear 7 is meshed with the first torque splitting driven gear 8 and the second torque splitting driven gear 9 simultaneously to realize primary flow splitting and secondary speed reduction; the first torque-dividing driven gear 8 and the second coaxial driving gear 12 are fixed on a third gear shaft 13, and the second torque-dividing driven gear 9 and the first coaxial driving gear 10 are fixed on a second gear shaft 11; the first coaxial driving gear 10 and the second coaxial driving gear 12 are meshed with a second coaxial driven gear 25 to realize primary parallel operation and three-stage speed reduction, and the second coaxial driven gear 25 is fixed on a first rotor output shaft 26; similarly, the second torque splitting driving gear 18 and the second driven bevel gear 15 are fixed on the fourth gear shaft 16, and the second torque splitting driving gear 18 is simultaneously meshed with the third torque splitting driven gear 17 and the fourth torque splitting driven gear 19 to realize primary flow splitting and secondary speed reduction; the third torque division driven gear 17 and the third coaxial driving gear 20 are fixed on a sixth gear shaft 23, the fourth torque division driven gear 19 and the fourth coaxial driving gear 21 are fixed on a fifth gear shaft 22, the third coaxial driving gear 20 and the fourth coaxial driving gear 21 are both meshed with the first coaxial driven gear 24, primary parallel operation and three-stage speed reduction are realized, and the second coaxial driven gear 24 is fixed on a second rotor output shaft 27.

The invention provides a torque-dividing transmission speed reducer for a coaxial helicopter.A motor output shaft 1 is connected with a power input shaft 3 through an overrunning clutch 2, two driving bevel gears (a first driving bevel gear 4 and a second driving bevel gear 14) are fixed on the power input shaft 3 and are respectively meshed with two driven bevel gears (a first driven bevel gear 5 and a second driven bevel gear 15) so as to realize reversing and torque dividing, and the small end faces of the two driven bevel gears (the first driven bevel gear 5 and the second driven bevel gear 15) are oppositely arranged so as to ensure that the two rotor shafts are reversely rotated.

Finally, the above embodiments are only intended to illustrate the technical solutions of the present invention and not to limit the present invention, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions, and all of them should be covered by the claims of the present invention.