CN202345911U - Coaxial dual-rotor helicopter - Google Patents
Coaxial dual-rotor helicopter Download PDFInfo
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- CN202345911U CN202345911U CN201120448353XU CN201120448353U CN202345911U CN 202345911 U CN202345911 U CN 202345911U CN 201120448353X U CN201120448353X U CN 201120448353XU CN 201120448353 U CN201120448353 U CN 201120448353U CN 202345911 U CN202345911 U CN 202345911U
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Abstract
The utility model discloses a coaxial dual-rotor helicopter. The coaxial dual-rotor helicopter comprises a rotor shaft mounted at the upper part of an airframe, the rotor shaft comprises an external rotation shat and an internal rotation shaft, the rotor shaft is provided with an upper rotor and a lower rotor, the internal rotation shaft and the external rotation shaft are interconnected by a bearing, the upper rotor is mounted on the internal rotation shaft, and the lower rotor is mounted on the external rotation shaft; the blade length of the upper rotor is less than that of the lower rotor; the upper rotor comprises four blades; and the lower rotor comprises three blades. With the technical scheme, the coaxial dual-rotor helicopter has a simple structure; by substantial improvement on the length, the amount, the rotation speed and the material of the blades on the upper rotor, an operation mechanism can be simple, and the danger of blade collision caused by interference between the upper and lower rotors is avoided; and simultaneously, the parasitic drag area of the two pairs of rotors is small, and thus the lifting power, the maximum level speed and the overall performance of the helicopter are all improved.
Description
Technical field
The utility model belongs to the technical field of aviation aircraft, relates to the technology of autogyro, and more particularly, the utility model relates to a kind of coaxial rotor helicopter.
Background technology
Helicopter is a kind ofly to produce lift and propulsive force and the aerocraft that flies by rotor, compares with fixed wing aircraft, and its important feature is that helicopter can be realized hovering.Mainly contain two types of single-rotor helicopter and twin-rotor helicopters:
Single-rotor helicopter generally adopts tail-rotor to offset the reactive torque that main rotor produces.An outstanding problem of single rotor tail-rotor helicopter is the fugitiveness of himself.Single-rotor helicopter is very big around the rotor inertia of rotor shaft, generally relies on tail-rotor fully and comes the balance reactive torque.Tail-rotor is the ultimate challenge of single-rotor helicopter flight safety, and main rotor runs out of steam, the helicopter landing of can also spinning; But in a single day tail-rotor runs out of steam, the commentaries on classics of will spinning of that helicopter, get out of hand.In addition, tail-rotor also consumes the engine power of quite a few.
Twin-rotor helicopter adopts the rotor of two contrarotations, by its arrangement mode, can be divided into lap siding, cross-arranging type, staggered form and close coupled type four major types.Coaxial rotor helicopter medicine essential characteristic is: two secondary identical rotors, be installed in one on the other on the same rotor shaft, and at regular intervals between two rotors.The hand of rotation of two secondary rotors is opposite, and their reactive torque can be cancelled each other.Like this, just do not need to have refilled tail-rotor.The differential change of the total distance of two rotors was accomplished about the directional control of helicopter leaned on.
Coaxial rotor helicopter major advantage is that whole power of driving engine all are used for driving rotor, the aerodynamic force symmetry, and hovering efficiency is high, and mechanical vibration are little, and noise is low.This helicopter can adopt the structure of No Tail Rotor, so also just need not adorn long tail boom, fuselage length also can shorten greatly.
The major defect of coaxial rotor helicopter is that steering unit is complicated.And since when flight the asymmetric lift that produces with retreating blade of advancing blade, the plane of rotation of rotor has the danger that causes blade to collide in a side generation intersection up and down.In addition, the useless resistance area of two secondary rotors is bigger, has so just limited the max level speed of helicopter.
The utility model content
The utility model provides a kind of coaxial rotor helicopter, its objective is to reduce the danger of rotor collision up and down, has less useless resistance area and and then acquisition higher lift coefficient simultaneously.
To achieve these goals, the technical scheme taked of the utility model is:
The coaxial rotor helicopter that the utility model provided; Comprise the rotor shaft that is installed in back; Said rotor shaft comprises outer shaft and interior rotating shaft, and said rotor shaft is provided with rotor and following rotor, interconnects through bearing between said interior rotating shaft and the outer shaft; The described rotor of going up is installed in the described interior rotating shaft, and described rotor down is installed on the described outer shaft; The said length that goes up the paddle length of rotor less than the blade of following rotor.
The described rotor of going up is installed four blades of gyratory directions well-distributed through propeller hub in the rotating shaft in described; Described rotor is down installed three blades of gyratory directions well-distributed through propeller hub on said outer shaft.
The said pitch of going up between rotor, the following rotor is controlled through last apparatus of automatic rotor oblique device, following apparatus of automatic rotor oblique device respectively; The said apparatus of automatic rotor oblique device of going up is installed between rotor and the following rotor, and said apparatus of automatic rotor oblique device down is installed in down the bottom of rotor.
Said outer shaft and interior rotating shaft are driven by the power transmission of driving engine through different drive ratios respectively.
The structure of described upward apparatus of automatic rotor oblique device, following apparatus of automatic rotor oblique device is identical, forms by spherical linkage or universal-joint, interior ring, outer shroud, toggle and some pull bars.
The transmitting ratio of described driving engine to outer shaft is greater than driving engine to interior rotating shaft transmitting ratio.
First cone gear is installed on the output shaft of said driving engine; And said first cone gear is meshed with outer transmission shaft cone gear and intermediate solid drive shaft cone gear respectively, and described outer transmission shaft cone gear is connected with outer shaft gear transmission on being installed in outer shaft through coaxial mounted cylindrical wheel; Described intermediate solid drive shaft cone gear is in transmission connection through coaxial mounted cylindrical wheel and the interior shaft gear that is installed in the interior rotating shaft.
Described coaxial rotor helicopter is provided with tail-rotor, and described tail-rotor is a duct formula tail-rotor, and its structure is that the tail slurry blade is embedded in the duct of tail, and the perforation direction of described duct is the elevation profile perpendicular to helicopter fuselage.
The utility model adopts technique scheme; It is simple in structure; Substantial improvements through to the carrying out of the length of last rotor blade, quantity, rotative speed, material makes steering unit simple, has avoided taking place up and down rotor and has interfered the danger that causes the blade collision; The useless resistance area of two secondary rotors is less simultaneously, has improved the Combination property of rising power, max level speed and the helicopter of helicopter.
Description of drawings
The mark of facing down among expressed content of each width of cloth accompanying drawing of this specification sheets and the figure is made brief description:
Fig. 1 is the planar structure scheme drawing of the upper and lower rotor in the utility model;
Fig. 2 is the structural representation of upper and lower apparatus of automatic rotor oblique device in the utility model;
Fig. 3 is the structural representation of the driving device in the utility model.
Be labeled as among the figure:
1, outer shaft, 2, interior rotating shaft, 3, go up rotor, 4, rotor down; 5, go up apparatus of automatic rotor oblique device, 6, apparatus of automatic rotor oblique device down, 7, first cone gear, 8, outer transmission shaft cone gear; 9, intermediate solid drive shaft cone gear, 10, the outer shaft gear, 11, the outer shaft gear.
The specific embodiment
Contrast accompanying drawing below,, the specific embodiment of the utility model is done further detailed explanation, inventive concept, the technical scheme of the utility model are had more complete, accurate and deep understanding to help those skilled in the art through description to embodiment.
Structure like the expressed the utility model of Fig. 1, Fig. 2 and Fig. 3; For a kind of coaxial rotor helicopter, comprise the rotor shaft that is installed in back, said rotor shaft comprises outer shaft 1 and interior rotating shaft 2; Said rotor shaft is provided with rotor 3 and following rotor 4; Interconnect through bearing between rotating shaft 2 and the outer shaft 1 in said, the described rotor 3 of going up is installed in the described interior rotating shaft 2, and described rotor 4 down is installed on the described outer shaft 1.
Because quite a few of the moment of torsion that following rotor 4 is produced is by the moment of torsion of last rotor 3 institute balance; The coaxial rotor helicopter is significantly smaller than common single rotor tail-rotor helicopter around the rotor inertia of axle; So not only improved the stability of helicopter; And reduced the required tail-rotor power of reactive torque that overcomes helicopter, it is good but power receives the use of the duct formula tail-rotor of dimensional restriction to be particularly suitable for performance.
In order to solve the problem that exists at the described present known technology of this specification sheets background technology part and to overcome its defective; Realize reducing the danger of rotor collision up and down; Have simultaneously less useless resistance area and and then obtain the goal of the invention of higher lift coefficient, the technical scheme that the utility model is taked is:
Extremely shown in Figure 3 like Fig. 1, the coaxial rotor helicopter that the utility model provided, the said length that goes up the paddle length of rotor 3 less than the blade of following rotor 4.
Compare with common single rotor tail-rotor helicopter, the use of last rotor 3 can improve the climbing performance of helicopter effectively.See that conversely under same lift designing requirement, the following rotor 4 of the coaxial rotor helicopter that is uneven in length can be done shortly than the rotor of common single rotor tail-rotor helicopter.
The concrete flight driver behavior of the coaxial rotor helicopter that is uneven in length and common single rotor tail-rotor helicopter are basic identical.In fact, the coaxial rotor helicopter that is uneven in length can maximally utilise existing single-rotor helicopter technology, need not do under the situation of very big technological improvement, improves the Combination property of helicopter.
The described rotor 3 of going up is installed four blades of well-distributed through propeller hub in the rotating shaft 2 in described; Described rotor 4 is down installed three blades of well-distributed through propeller hub on said outer shaft 1.
Blade quantity through increasing last rotor 3 improves the rotor real area, and the lift that following rotor 4 was produced in the lift that rotor 3 is produced in its rotor disk area compared with homalographic is big.
Saidly go up rotor 3, the pitch between the rotor 4 is respectively through last apparatus of automatic rotor oblique device 5, apparatus of automatic rotor oblique device 6 controls down down; The said apparatus of automatic rotor oblique device 5 of going up is installed between rotor 3 and the following rotor 4, and said apparatus of automatic rotor oblique device 6 down is installed in down the bottom of rotor 4.
The structure of described upward apparatus of automatic rotor oblique device 5, following apparatus of automatic rotor oblique device 6 is identical, forms by spherical linkage or universal-joint, interior ring, outer shroud, toggle and some pull bars.
The structural principle of described upward apparatus of automatic rotor oblique device 5, following apparatus of automatic rotor oblique device 6 and the auto-bank unit of common single rotor tail-rotor helicopter are basic identical.The interior ring of auto-bank unit then is connected through bearing with outer shroud, can be free to slide between interior ring and the outer shroud.The interior ring of last apparatus of automatic rotor oblique device 5 links to each other with interior rotating shaft 2 through toggle, rotates synchronously thereupon, and links to each other with the distance-variable rocker arm of the blade of last rotor 3 through pitch-change-link.The interior ring of following apparatus of automatic rotor oblique device 6 then through control operating rod with always link to each other with collective-pitch lever with jociey stick in the driving compartment apart from sleeve.Last apparatus of automatic rotor oblique device 5, the outer shroud of apparatus of automatic rotor oblique device 6 all links to each other with outer shaft 1 through toggle respectively down; Rotate synchronously with outer shaft 1; And there are some isometric struts that they are linked to each other; So that go up apparatus of automatic rotor oblique device 5, apparatus of automatic rotor oblique device 6 realization synchronization liftings, inclination synchronously down, remain parastate.The outer shroud of following apparatus of automatic rotor oblique device 6 also links to each other with the distance-variable rocker arm of the blade of following rotor 4 through pitch-change-link.
The same with common single rotor tail-rotor helicopter, the front and back of helicopter and the sporting flying of left and right directions realize that through cyclic pitch control helicopter rises thereupon or descends and realizes apart from handling through total.
Said outer shaft 1 is driven by the power transmission of driving engine through different drive ratios respectively with interior rotating shaft 2.
The transmitting ratio of described driving engine to outer shaft 1 is greater than driving engine to interior rotating shaft 2 transmitting ratios.Promptly go up the rotating speed of the rotating speed of rotor 3 greater than following rotor 4.
The utility model is in the scope that design allows; The rotative speed of the blade of short last rotor 3 can be faster than the paddle of following rotor 4, and it is bigger than the lift that rotor 4 under in homalographic is produced therefore to go up lift that rotor 3 produces in the rotor disk area that its blade rotates.When hovering; The wake flow of last rotor 3 can make the downdraft toe-in of rotor 3; So in fact the area that following rotor 4 is influenced by rotor 3 is less than the rotor disk area of rotor 3, thereby go up the rotor disk area of effective rotor disk area sum of rotor 3, following rotor 4 greater than following rotor 4.
Through first cone gear 7, divide two-way to pass to outer shaft 1 and interior rotating shaft 2 motion of driving engine, and, realize that different rotating speed needs through different transmitting ratios.
Obviously, in Fig. 3, two transmitting ratios are inequality.
Described coaxial rotor helicopter is provided with tail-rotor, and described tail-rotor is a duct formula tail-rotor, and its structure is that the tail slurry blade is embedded in the duct of tail, and the perforation direction of described duct is the elevation profile perpendicular to helicopter fuselage.The course of helicopter is then controlled through tail-rotor.
Because the use of tail-rotor, the coaxial rotor helicopter that is uneven in length do not need the complicated course control system of existing coaxial rotor helicopter.
Driving engine is identical with the helicopter of conventional single rotor magnetic tape trailer oar to the driving of tail-rotor.The major advantage of duct formula tail-rotor is its blade in the duct that embeds tail, and it is less influenced by extraneous interference in air flow, and noise is low, and is difficult for the accident of hurting sb.'s feelings, hitting thing, and is fool proof during nap of the earth flight.The major defect of duct formula tail-rotor is the size that has increased tail.Tail dimension is the overall performance of affects aircraft too, and too little but duct formula tail-rotor is done, its horsepower output or deboost often can not satisfy the requirement of general single-rotor helicopter again.Because the reactive torque of the coaxial helicopter that is uneven in length that the utility model provided is less relatively, be particularly suitable for the use of duct formula tail-rotor.
The utility model is simple in structure; Improving of length through upper and lower rotor blade, quantity, rotative speed, material; Steering unit is simple; Avoided upper and lower rotor to interfere, cause the danger of blade collision, the useless resistance area of two secondary rotors is less simultaneously, has improved the max level speed of helicopter and the Combination property of helicopter.
Combine accompanying drawing that the utility model has been carried out exemplary description above; Obviously the concrete realization of the utility model does not receive the restriction of aforesaid way; As long as adopted the method design of the utility model and the improvement of the various unsubstantialities that technical scheme is carried out; Or the design of the utility model and technical scheme are directly applied to other occasion without improving, all within the protection domain of the utility model.
Claims (8)
1. coaxial rotor helicopter; Comprise the rotor shaft that is installed in back; Said rotor shaft comprises outer shaft (1) and interior rotating shaft (2), and said rotor shaft is provided with rotor (3) and following rotor (4), interconnects through bearing between said interior rotating shaft (2) and the outer shaft (1); The described rotor (3) of going up is installed in the described interior rotating shaft (2), and described rotor (4) down is installed on the described outer shaft (1);
It is characterized in that:
The said length that goes up the paddle length of rotor (3) less than the blade of following rotor (4).
2. according to the described coaxial rotor helicopter of claim 1, it is characterized in that: described upward rotor (3) rotating shaft in described (2) is gone up through propeller hub four blades of gyratory directions well-distributed is installed; Described rotor (4) is down gone up through propeller hub at said outer shaft (1) three blades of gyratory directions well-distributed is installed.
3. according to claim 1 or 2 described coaxial rotor helicopters; It is characterized in that: the said pitch of going up between rotor (3), the following rotor (4) is controlled through last apparatus of automatic rotor oblique device (5), following apparatus of automatic rotor oblique device (6) respectively; The said apparatus of automatic rotor oblique device (5) of going up is installed between rotor (3) and the following rotor (4), and said apparatus of automatic rotor oblique device (6) down is installed in down the bottom of rotor (4).
4. according to claim 1 or 2 described coaxial rotor helicopters, it is characterized in that: said outer shaft (1) and interior rotating shaft (2) are driven by the power transmission of driving engine through different drive ratios respectively.
5. according to claim 1 or 2 described coaxial rotor helicopters; It is characterized in that: the structure of described upward apparatus of automatic rotor oblique device (5), following apparatus of automatic rotor oblique device (6) is identical, forms by spherical linkage or universal-joint, interior ring, outer shroud, toggle and some pull bars.
6. according to claim 1 or 2 described coaxial rotor helicopters, it is characterized in that: the transmitting ratio of described driving engine to outer shaft (1) is greater than driving engine to interior rotating shaft (2) transmitting ratio.
7. according to claim 1 or 2 described coaxial rotor helicopters; It is characterized in that: first cone gear (7) is installed on the output shaft of said driving engine; And said first cone gear (7) is meshed with outer transmission shaft cone gear (8) and intermediate solid drive shaft cone gear (9) respectively, and described outer transmission shaft cone gear (8) is in transmission connection through coaxial mounted cylindrical wheel and the outer shaft gear (10) that is installed on the outer shaft (1); Described intermediate solid drive shaft cone gear (9) is in transmission connection through coaxial mounted cylindrical wheel and the interior shaft gear (11) that is installed in the interior rotating shaft (2).
8. according to claim 1 or 2 described coaxial rotor helicopters; It is characterized in that: described coaxial rotor helicopter is provided with tail-rotor; Described tail-rotor is a duct formula tail-rotor; Its structure is that the tail slurry blade is embedded in the duct of tail, and the perforation direction of described duct is perpendicular to the elevation profile of helicopter fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120448353XU CN202345911U (en) | 2011-11-14 | 2011-11-14 | Coaxial dual-rotor helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120448353XU CN202345911U (en) | 2011-11-14 | 2011-11-14 | Coaxial dual-rotor helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202345911U true CN202345911U (en) | 2012-07-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201120448353XU Expired - Fee Related CN202345911U (en) | 2011-11-14 | 2011-11-14 | Coaxial dual-rotor helicopter |
Country Status (1)
| Country | Link |
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| CN (1) | CN202345911U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102490898A (en) * | 2011-11-14 | 2012-06-13 | 李杏健 | Coaxial dual-rotor helicopter |
| CN104743109A (en) * | 2015-04-17 | 2015-07-01 | 何春旺 | Power system and aircraft |
| CN106927033A (en) * | 2017-04-14 | 2017-07-07 | 天津京东智联科技发展有限公司 | A kind of vertical coaxial dual-rotor helicopter |
| CN108327899A (en) * | 2018-01-29 | 2018-07-27 | 陈铭 | A kind of coaxial double-oar helicopter rotor method for arranging and coaxial double-oar helicopter up and down |
| CN110370869A (en) * | 2019-08-18 | 2019-10-25 | 王永成 | The more travel pattern vehicles in water sky land |
-
2011
- 2011-11-14 CN CN201120448353XU patent/CN202345911U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102490898A (en) * | 2011-11-14 | 2012-06-13 | 李杏健 | Coaxial dual-rotor helicopter |
| CN104743109A (en) * | 2015-04-17 | 2015-07-01 | 何春旺 | Power system and aircraft |
| CN104743109B (en) * | 2015-04-17 | 2018-03-27 | 珠海磐磊智能科技有限公司 | Dynamical system and aircraft |
| CN106927033A (en) * | 2017-04-14 | 2017-07-07 | 天津京东智联科技发展有限公司 | A kind of vertical coaxial dual-rotor helicopter |
| CN106927033B (en) * | 2017-04-14 | 2023-10-13 | 天津京东智联科技发展有限公司 | Vertical coaxial double-rotor aircraft |
| CN108327899A (en) * | 2018-01-29 | 2018-07-27 | 陈铭 | A kind of coaxial double-oar helicopter rotor method for arranging and coaxial double-oar helicopter up and down |
| CN110370869A (en) * | 2019-08-18 | 2019-10-25 | 王永成 | The more travel pattern vehicles in water sky land |
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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: 20120725 Termination date: 20141114 |
|
| EXPY | Termination of patent right or utility model |