CN202624632U - Coaxial double-rotor structure of helicopter - Google Patents
Coaxial double-rotor structure of helicopter Download PDFInfo
- Publication number
- CN202624632U CN202624632U CN 201220234930 CN201220234930U CN202624632U CN 202624632 U CN202624632 U CN 202624632U CN 201220234930 CN201220234930 CN 201220234930 CN 201220234930 U CN201220234930 U CN 201220234930U CN 202624632 U CN202624632 U CN 202624632U
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- quill shaft
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Abstract
The utility model provides a coaxial double-rotor structure of a helicopter. The structure comprises a quill shaft, a long rotor arranged at the top of the quill shaft and a short rotor arranged under the long rotor. The structure is characterized in that the long rotor comprises a long rotor hub and blades distributed on the outer diameter of the long rotor hub; the quill shaft comprises an inner shaft, an outer shaft and a casing which are arranged sequentially from inside to outside; and the short rotor comprises a short rotor hub and blades distributed on the outer diameter of the short rotor hub; and the long rotor and the short rotor are distributed vertically. Compared with the prior art, the improved coaxial double-rotor structure of the helicopter has the advantages that the collision probability of the two pairs of rotors is reduced, the length of the quill shaft is shortened, the wind resistance of the helicopter is reduced, and the performance of the helicopter is improved.
Description
Technical field
The utility model relates to the vehicle technology field, especially a kind of coaxial double-rotary wing structure of improved type helicopter.
Background technology
The coaxial double-rotary wing helicopter does not need tail-rotor to come the moment on the balancing helicopter horizontal direction, maintains easily, and stronger viability is arranged; The aerodynamic characteristic symmetry, manoevreability is good, and under the situation of using same engine, the lift of two secondary close coupled type rotors is bigger by 12% than the rotor lift of single rotor/tail-rotor layout; Be easy to during maneuvering flight handle, when changing course, co-axial helicopter is easy to keep the flying height of helicopter, also has the compact advantage of oad simultaneously.
Yet existing coaxial double-rotary wing helicopter rotor blade size up and down all is the same, has certain shortcoming: the identical rotor of two metaplasm leaf length one on the other, blade can not collided when flying usually; But under some special situation; As running into unexpected change wind awing, the motor-driven value of overstepping the extreme limit is when blade distortion or damage; The aerodynamic force, centnifugal force and the gravity that act on the blade will lose original balance, thereby depart from normal running orbit and bump.Because the cause of asymmetric lift; The plane of rotation of the rotor up and down of contrarotation has the tendency in a side " collision "; This has further increased the requirement of spacing between the rotor up and down, and if bring when having " collision " tendency one side to turn, must be softr than turning to opposite side; Otherwise the serious like this accident of rotor blade collision up and down will take place, thereby cause the fatal crass.The length of driving system quill shaft is long more a lot of than original (single-rotor helicopter), and quill shaft is not only wanted transmitted power, and the total distance, cycle that also will transmit top rotor have cooresponding difficulty apart from control in machine design.
Given this, be necessary to provide a kind of coaxial double-rotary wing structure of improved type helicopter, solve above-mentioned technical matters.
Summary of the invention
The technical matters that the utility model solved is to provide a kind of coaxial double-rotary wing structure of improved type helicopter, solve in the prior art coaxial double-rotary wing up and down rotor blade collide easily, and to quill shaft length and the high problem of material requirements.
For solving the problems of the technologies described above; The utility model adopts following technical scheme: a kind of coaxial double-rotary wing structure of improved type helicopter; Comprise quill shaft, be positioned at the quill shaft top long rotor, be positioned at the short rotor of long rotor below; Said long rotor comprises long rotor hub and is distributed in the sweep leaf of long rotor hub external diameter, and said quill shaft is provided with interior axle, outer shaft, sleeve from inside to outside successively, and said short rotor comprises short rotor hub and is distributed in the paddle of short rotor hub external diameter; It is characterized in that said long rotor and the vertically arrangement up and down of short rotor, the sweep leaf is 1:0.618 with the length ratio of paddle.
Short rotor can be through increasing the moment that blade width, rotative speed or blade quantity are come the long rotor of balance, thereby keep the stable of helicopter, can exchange about long as required rotor and the weak point rotor.
Compared with prior art; The probability of the coaxial double-rotary wing structure decrease two secondary rotor collisions of the said improved type helicopter of the utility model; Thereby the length that shortens the driving system quill shaft has reduced the requirement of quill shaft to material, has effectively reduced body height, body weight and the structural focus of whole helicopter, has reduced the windage of whole helicopter; Thereby accelerated helicopter speed, improved the Combination property of aircraft.
[description of drawings]
Fig. 1 is the coaxial double-rotary wing structural representation of the said improved type helicopter of the utility model.
[specific embodiment]
See also the coaxial double-rotary wing structure 100 of improved type helicopter shown in Figure 1; Adopt not isometric up and down rotor blade structure; Comprise long rotor 1, short rotor 2, quill shaft 3; Said long rotor comprises sweep leaf 11, long rotor hub 12, and axle 33, outer shaft 32, sleeve 31 in said quill shaft comprises, said short rotor comprise paddle 21, short rotor hub 22.
Said long rotor 1 is different with the blade length of short rotor 2, and sweep leaf 11 is 1:0.618 (reference value) with paddle 21 length ratio.
Said long rotor 1, short rotor 2 are vertically arranged, and link to each other with Helicopter Transmission System through quill shaft 3.
Said long rotor 1, short rotor 2 can replace up and down according to type and actual conditions, are used for different type of machines.
The coaxial double-rotary wing structure of the described improved type helicopter of the utility model passes through the not isometric structure of rotor up and down, has realized reducing the probability of two secondary rotors collisions, shortens the effect of the length of driving system quill shaft, has improved the Combination property of helicopter.
The above; It only is the most preferred embodiment of the utility model; Be not that the utility model is done any pro forma restriction, any those of ordinary skill in the art are not breaking away under the utility model technical scheme scope situation; Utilize the method content of above-mentioned announcement that the utility model technical scheme is made many possible changes and modification, all belong to the scope of claims protection.
Claims (2)
1. the coaxial double-rotary wing structure of a helicopter; Comprise quill shaft, be positioned at the quill shaft top long rotor, be positioned at the short rotor of long rotor below; It is characterized in that: said long rotor comprises long rotor hub and is distributed in the sweep leaf of long rotor hub external diameter; Said quill shaft is provided with interior axle, outer shaft, sleeve from inside to outside successively, and said short rotor comprises short rotor hub and is distributed in the paddle of short rotor hub external diameter.
2. the coaxial double-rotary wing structure of helicopter according to claim 1 is characterized in that: said long rotor is vertically arranged up and down with short rotor, and the length of said sweep leaf and paddle is than being 1:0.618.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220234930 CN202624632U (en) | 2012-05-24 | 2012-05-24 | Coaxial double-rotor structure of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220234930 CN202624632U (en) | 2012-05-24 | 2012-05-24 | Coaxial double-rotor structure of helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202624632U true CN202624632U (en) | 2012-12-26 |
Family
ID=47377856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220234930 Expired - Fee Related CN202624632U (en) | 2012-05-24 | 2012-05-24 | Coaxial double-rotor structure of helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202624632U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104129498A (en) * | 2014-07-23 | 2014-11-05 | 中国航天空气动力技术研究院 | Rotor wing control mechanism for coaxial helicopter |
| CN104554719A (en) * | 2013-10-23 | 2015-04-29 | 田刚印 | Rotor wing driving method and device |
| CN104554717A (en) * | 2013-10-23 | 2015-04-29 | 田刚印 | Rotor wing driving system |
| CN104743109A (en) * | 2015-04-17 | 2015-07-01 | 何春旺 | Power system and aircraft |
| CN112173097A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Coaxial double-rotor wing with unequal diameters |
-
2012
- 2012-05-24 CN CN 201220234930 patent/CN202624632U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554719A (en) * | 2013-10-23 | 2015-04-29 | 田刚印 | Rotor wing driving method and device |
| CN104554717A (en) * | 2013-10-23 | 2015-04-29 | 田刚印 | Rotor wing driving system |
| CN104554717B (en) * | 2013-10-23 | 2016-09-28 | 田刚印 | rotor drive system |
| CN104129498A (en) * | 2014-07-23 | 2014-11-05 | 中国航天空气动力技术研究院 | Rotor wing control mechanism for coaxial helicopter |
| CN104743109A (en) * | 2015-04-17 | 2015-07-01 | 何春旺 | Power system and aircraft |
| CN112173097A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Coaxial double-rotor wing with unequal diameters |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121226 Termination date: 20140524 |