CN205707340U - A kind of helicopter reductor - Google Patents
A kind of helicopter reductor Download PDFInfo
- Publication number
- CN205707340U CN205707340U CN201620391552.4U CN201620391552U CN205707340U CN 205707340 U CN205707340 U CN 205707340U CN 201620391552 U CN201620391552 U CN 201620391552U CN 205707340 U CN205707340 U CN 205707340U
- Authority
- CN
- China
- Prior art keywords
- driven gear
- reductor
- output shaft
- gear
- shaft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses a kind of helicopter reductor, belong to aircraft down machine field, being used for solving common reductor can not input by multiaxis, the problem that twin shaft exports and outbound course is contrary.It includes reductor body, this body side surface of reductor is provided with power shaft, power shaft half embeds reductor, and this is internal, power shaft embeds reductor body one end and is provided with driving gear, reductor body lower end is provided with base, base is provided with the first output shaft, first output shaft lower end is cased with the first driven gear, first driven gear and the first output shaft are connected with keyway by key, first driven gear is arranged over the second driven gear, first driven gear and the second driven gear are oppositely arranged, second driven gear upper end is provided with the second output shaft, second driven gear and the second output shaft are connected by bolt matching thread.The technical program, simple in construction, low cost, can input by multiaxis, twin shaft output and outbound course are contrary.
Description
Technical field
This utility model belongs to aircraft down machine field, specifically, is a kind of helicopter reductor.
Background technology
Helicopter Main Reducer drive mechanism, as one of the three big critical components of helicopter, receives much concern always.Helicopter Main subtracts
The effect of speed device is that output and the output speed of electromotor are delivered to rotor according to a certain percentage up, is engine power
Export indispensable transmission part, be also unique delivering path.And driving engine is only single input, single export structure,
It is not met by the requirement of multi input, dual output.Further, external certain type utility helicopter, in its accessory drive gear, directly
Input gear engages multiple output gear, gives, through multistage bending moment, the power that the offer of each adnexa is bigger with output gear.So,
Adnexa output speed is required high, causes that attachment mechanism is complicated, volume big, high in cost of production problem.
Utility model content
This utility model purpose is intended to provide the input of a kind of multiaxis, the helicopter reductor of two-way output.
For realizing above-mentioned technical purpose, the technical solution adopted in the utility model is as follows:
A kind of helicopter reductor, including reductor body, described this body side surface of reductor is provided with power shaft, described power shaft
Half embeds reductor, and this is internal, and described power shaft embeds reductor body one end and is provided with driving gear, described reductor body lower end
Being provided with base, described base is provided with the first output shaft, and described first output shaft lower end is cased with the first driven gear, and described first
Driven gear and the first output shaft are connected with keyway by key, and described first driven gear is arranged over the second driven gear,
Described first driven gear and the second driven gear are oppositely arranged, and described second driven gear upper end is provided with the second output shaft, described
Second driven gear and the second output shaft are connected by bolt matching thread, and described second driven gear and the second output sleeve are in the
Outside one output shaft, described second output shaft and the first output shaft arranged coaxial, described driving gear is positioned at the first driven gear and
Between two driven gears.
Use technique scheme utility model, electromotor through power shaft and driving gear, driving gear respectively with first from
Moving gear and the engagement of the second driven gear, be delivered to the first output shaft and the second output shaft respectively by power；Due to the first driven tooth
Wheel and the second driven gear are oppositely arranged, and driving gear is positioned between the two, and under identical driving gear drives, first is driven
Gear and the second driven gear rotation direction are contrary, and then drive the first output shaft and the second output shaft to rotate towards different directions respectively,
Realize the two-way output of double output shaft.
Preferably, described power shaft at least 4, described power shaft matches two-by-two and is mounted opposite on reductor body, described defeated
Enter axle sleeve and have clutch shaft bearing.
Multiple power shafts can provide bigger power in the case of rotating speed is identical, arranges clutch shaft bearing and reduces power shaft rotation
Time with the friction between reductor body.
Preferably, described driving gear is angular wheel, and described first driven gear is the gloomy helical gear of Green, described second from
Moving gear is the gloomy helical gear of Green, and described first driven gear and the second driven gear profile of tooth specification are identical.
Angular wheel helical gear gloomy with Green is more fitted in profile of tooth, and engagement is more tight, driving gear when reducing operation
And between cog impact force degree between the first driven gear and the second driven gear.
Preferably, described first output shaft lower end is cased with the second bearing.
Make the first output shaft and reductor body between the two will not direct friction, cause damage.
Preferably, it is provided with the 3rd bearing between described second output shaft upper end and the first output shaft.
Add the second output shaft rotation stability.
Preferably, it is provided with the 4th bearing between described second output shaft and reductor body.
Further increase the stability of the second output shaft rotation, make the second bearing directly will not rub with reductor body when rotating
Wipe.
Compared to existing technology, simple in construction, low cost, energy multiaxis input, twin shaft output and outbound course are contrary for this utility model.
Accompanying drawing explanation
This utility model can be further illustrated by the nonlimiting examples that accompanying drawing is given；
Fig. 1 is this utility model one helicopter speed reducer structure schematic diagram；
Main element symbol description is as follows:
Reductor body 1, power shaft 2, driving gear 3, base the 4, first output shaft the 5, first driven gear 6, second from
Moving gear the 7, second output shaft 8, clutch shaft bearing the 9, second bearing the 10, the 3rd bearing the 11, the 4th bearing 12.
Detailed description of the invention
In order to make those skilled in the art that this utility model be may be better understood, below in conjunction with the accompanying drawings with embodiment to this practicality
New technique scheme further illustrates.
As it is shown in figure 1, a kind of helicopter reductor, including reductor body 1, reductor body 1 side is provided with power shaft 2,
Power shaft 2 half embeds in reductor body 1, and power shaft 2 embeds reductor body 1 one end and is provided with driving gear 3, reductor
Body 1 lower end is provided with base 4, and base 4 is provided with the first output shaft 5, and the first output shaft 5 lower end is cased with the first driven gear 6,
First driven gear 6 is connected with keyway by key with the first output shaft 5, and it is driven that the first driven gear 6 is arranged over second
Gear 7, the first driven gear 6 and the second driven gear 7 be oppositely arranged, and the second driven gear 7 upper end is provided with the second output shaft 8,
Second driven gear 7 is connected by bolt matching thread with the second output shaft 8, and the second driven gear 7 and the second output shaft 8 overlap
Outside the first output shaft 5, the second output shaft 8 and the first output shaft 5 arranged coaxial, driving gear 3 is positioned at the first driven gear
7 and second between driven gear 8.
In preferred embodiment, power shaft 2 is 4, and power shaft 2 matches two-by-two and is mounted opposite, and power shaft 2 is cased with the first axle
Hold 9.
Driving gear 3 is angular wheel, and the first driven gear 6 is the gloomy helical gear of Green, and the second driven gear 7 is that Green is gloomy
Helical gear, the first driven gear 6 is identical with the second driven gear 7 profile of tooth specification.
First output shaft 5 lower end is cased with the second bearing 10.
It is provided with the 3rd bearing 11 between second output shaft 8 upper end and the first output shaft 5.
It is provided with the 4th bearing 12 between second output shaft 8 and reductor body 1.
A kind of helicopter reductor provided this utility model above is described in detail.The explanation of specific embodiment is simply
It is adapted to assist in understanding method of the present utility model and core concept thereof.It should be pointed out that, for those skilled in the art
For, on the premise of without departing from this utility model principle, it is also possible to this utility model is carried out some improvement and modification, these
Improve and modification also falls in this utility model scope of the claims.
Claims (6)
1. a helicopter reductor, including reductor body, it is characterised in that: described this body side surface of reductor is provided with input
Axle, described power shaft half embeds reductor, and this is internal, and described power shaft embeds reductor body one end and is provided with driving gear, described
Reductor body lower end is provided with base, and described base is provided with the first output shaft, and it is driven that described first output shaft lower end is cased with first
Gear, described first driven gear and the first output shaft be connected with keyway by key, and described first driven gear is arranged over
Second driven gear, described first driven gear and the second driven gear be oppositely arranged, and described second driven gear upper end is provided with
Two output shafts, described second driven gear and the second output shaft are connected by bolt matching thread, described second driven gear and the
Two output sleeves are outside the first output shaft, and described second output shaft and the first output shaft arranged coaxial, described driving gear is positioned at
Between one driven gear and the second driven gear.
A kind of helicopter reductor the most according to claim 1, it is characterised in that: described power shaft at least 4, institute
Stating power shaft to match two-by-two and be mounted opposite on reductor body, described power shaft is cased with clutch shaft bearing.
A kind of helicopter reductor the most according to claim 2, it is characterised in that: described driving gear is angular wheel,
Described first driven gear is the gloomy helical gear of Green, and described second driven gear is the gloomy helical gear of Green, described first driven
Gear and the second driven gear profile of tooth specification are identical.
A kind of helicopter reductor the most according to claim 3, it is characterised in that: described first output shaft lower end is cased with
Second bearing.
A kind of helicopter reductor the most according to claim 4, it is characterised in that: described second output shaft upper end and the
The 3rd bearing it is provided with between one output shaft.
A kind of helicopter reductor the most according to claim 5, it is characterised in that: described second output shaft and reductor
The 4th bearing it is provided with between body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620391552.4U CN205707340U (en) | 2016-05-04 | 2016-05-04 | A kind of helicopter reductor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620391552.4U CN205707340U (en) | 2016-05-04 | 2016-05-04 | A kind of helicopter reductor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205707340U true CN205707340U (en) | 2016-11-23 |
Family
ID=57331774
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620391552.4U Expired - Fee Related CN205707340U (en) | 2016-05-04 | 2016-05-04 | A kind of helicopter reductor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205707340U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216610A (en) * | 2016-12-12 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of rotor wing rotation driving mechanism |
-
2016
- 2016-05-04 CN CN201620391552.4U patent/CN205707340U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216610A (en) * | 2016-12-12 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of rotor wing rotation driving mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161123 Termination date: 20190504 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |