CN2717814Y - Coaxle remote-control double-rotor heligiro - Google Patents
Coaxle remote-control double-rotor heligiro Download PDFInfo
- Publication number
- CN2717814Y CN2717814Y CN 200420083294 CN200420083294U CN2717814Y CN 2717814 Y CN2717814 Y CN 2717814Y CN 200420083294 CN200420083294 CN 200420083294 CN 200420083294 U CN200420083294 U CN 200420083294U CN 2717814 Y CN2717814 Y CN 2717814Y
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- Prior art keywords
- rotor
- goblin
- rotary wing
- connecting rod
- coaxial double
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- Expired - Lifetime
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- 230000000087 stabilizing effect Effects 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 claims description 4
- 230000000694 effects Effects 0.000 description 3
- 230000000737 periodic effect Effects 0.000 description 3
- 230000000116 mitigating effect Effects 0.000 description 2
- 241000220317 Rosa Species 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Abstract
The utility model relates to a remote-control model helicopter, particularly a remote-control model helicopter which uses an upper and a lower rotor wings to rotate in forward and backward two direction to produce the changing of the lift force and the changing of the direction, which comprises a frame, rotor wings, a drive motor, a drive gear cluster, and a control steering gear. The drive motor and the control steering gear are respectively mounted on the platform of the frame; the drive gear cluster is arranged under the platform of the frame; the positive rotor wing and an inclined disc are directly connected through a connecting rod with double-ball head; the negative rotor wing and a stable hammer are connected through an L-shaped connecting rod. Compared with the prior art, as the positive rotor wing of the utility model and the inclined disc are directly connected through a connecting rod with double-ball head, a stable proportional relation is formed; as the negative rotor wing and the stable hammer are connected through an L-shaped connecting rod, the stable proportional relation of the stable hammer and the rotor wings is solved; when the rotor wings are unstable, the rotor wings can be easily corrected through the stable hammer; accordingly, the stability of the negative rotor wing is improved, and the flying stability of the remote-control helicopter is improved.
Description
Technical field
The utility model relates to a kind of remote control model helicopter, and two pairs of rotors are done positive and negative rotation and produced lift variation and the remote control model helicopter of direction change about especially a kind of the utilization.
Background technology
The characteristics of coaxial double-rotary wing RC Goblin are: with two pairs of rotors on an axis, a pair of is positive rotation, and another offsets the derotation power that produces when two pairs of rotors rotate thus to being despining.When two pairs of rotors quickened simultaneously or slow down, helicopter rose or descends.When a pair of rotor acceleration, when another slowed down to rotor, helicopter just turned to.Positive rotor is made periodic angle of attack variation under the effect of tilting frame, generation is advanced or retreated therefrom, and the left side is moved or the right side is moved.The coaxial double-rotary wing RC Goblin mostly is relatively large oily power coaxial double-rotary wing RC Goblin in the market, and less have an electronic coaxial double-rotary wing line traffic control helicopter.Oil power coaxial double-rotary wing RC Goblin is big because of danger, cost is high, productive output is low, complex process can not form mass selling; Electronmotive Force coaxial double-rotary wing RC Goblin because of adopting the line traffic control mode, is experienced and lost untrammeled remote control amusement, and has been reduced the recreational of product.
Summary of the invention
The purpose of this utility model is to provide a kind of coaxial double-rotary wing RC Goblin, and its technical matters that will solve is to improve the flight stability and the ease for operation of RC Goblin.
For the utility model that achieves the above object adopts following technical scheme: the coaxial double-rotary wing RC Goblin, comprise frame, rotor, drive motor, driving gear set and control steering wheel, described drive motor and control steering wheel all are assemblied on the framework platform, driving gear set is assemblied in the framework platform below, adopt two ball head connecting rod direct connections between its positive rotor and the tilting frame, adopt L type connecting rod to connect between the derotation wing and the stabilizing hammer.
Be fixed with two motors on the framework platform described in the utility model.
The dextrorotation power gear of driving gear set described in the utility model and derotation power gear all are located at the transmission that is meshed with two motor gears respectively of framework platform below.
Two control steering wheels described in the utility model become 90 ° to be installed on the framework platform.
Two steering wheels of helicopter described in the utility model are connected with the tilting frame connecting rod respectively.
Rotor employing described in the utility model is combined into rotor and rotor chuck the structure of parts.
The assembly clearance of rotor described in the utility model and rotating head is: 0.1mm～0.8mm.
Two ball head connecting rods of positive rotor described in the utility model and tilting frame are the two ball head connecting rods of diplopore and become inverted trapezoidal structure.
The utility model compared with prior art because positive rotor and tilting frame adopt two ball head connecting rod direct connections to get up, forms a pair of stable proportionate relationship.Tilting frame produces inclination being promoted by steering wheel, this banking motion is delivered to positive rotor by connecting rod, make positive rotor produce periodic angle of attack variation, the proportionate relationship that is connected to form of two bulbs, reduced when making the motion amplitude of tilting frame be delivered to main rotor by connecting rod, that is to say the very mitigation that the action of main rotor when left and right sides sidesway and forward-reverse becomes, so just make helicopter can both keep a kind of smooth flight posture aloft all the time; And the derotation wing adopts L type connecting rod to be connected with the stabilizing hammer device that plays the balance and stability effect, has solved stabilizing hammer the stable ratio of rotor is closed.When rotor is unstable, can just be stabilized hammer very easily and corrects.This lever Billy relation that this L type connecting rod forms has improved the stability of the derotation wing, thereby has improved the flight stability of RC Goblin.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is a three-dimensional decomposition texture scheme drawing of the present utility model.
The specific embodiment
Embodiment is described in further detail the utility model below in conjunction with accompanying drawing.
As shown in Figure 1 and Figure 2, coaxial double-rotary wing RC Goblin of the present utility model, comprise frame 24, rotor 6,12, drive motor 17, driving gear set and control steering wheel (servo) 23, drive motor 17 and control steering wheel (servo) 23 all are assemblied on the framework platform 24, driving gear set is assemblied in framework platform 24 belows, adopt two ball head connecting rod 22 direct connections between its positive rotor 12 and the tilting frame 16, two ball head connecting rods 22 are for the two ball head connecting rods of diplopore and become inverted trapezoidal structure, adopt L type connecting rod 3 to connect between the derotation wing 6 and the stabilizing hammer 1.
Be fixed with two motors 17 on the framework platform 24 of the present utility model, the dextrorotation power gear 27 of driving gear set and derotation power gear 26 all are located at framework platform 24 belows, and transmission is meshed with two motor gears respectively.Two control steering wheel (servo) 23 one-tenth 90 ° are installed on the framework platform 24, and two steering wheels 23 of helicopter are connected with tilting frame connecting rod 22 respectively.
Rotor of the present utility model adopts the structure that rotor and rotor chuck is combined into parts, and the assembly clearance of rotor and rotating head is: 0.1mm～0.8mm.Rotor and rotor chuck are merged into parts, cancel the swing of rotor in plane of rotation, improved the conformity of production of main rotor like this, reduced the assembly error of main rotor.The assembly clearance of rotor and rotating head is to test by experiment, can effectively offset the vibration of rotor, promotes the stability of aircraft.
The derotation wing 6 of the present utility model adopts L type connecting rod to be connected with stabilizing hammer 1 device that plays the balance and stability effect, has solved the stable proportionate relationship of 1 pair of rotor of stabilizing hammer.When rotor is unstable, can just be stabilized 1 hammer very easily and corrects.This lever Billy that this L type connecting rod forms concerns, has improved the stability of the derotation wing.
Two ball head connecting rod 22 direct connections of positive rotor 12 of the present utility model and tilting frame 16 usefulness get up, and form a pair of stable proportionate relationship.Tilting frame 16 is being promoted by steering wheel 23 and is producing inclination, and this banking motion is delivered to positive rotor 12 by connecting rod, makes positive rotor 12 produce periodic angle of attack variation.The proportionate relationship that is connected to form of two bulbs, reduced when making the motion amplitude of tilting frame 16 be delivered to main rotor by connecting rod, that is to say the very mitigation that the action of main rotor when left and right sides sidesway and forward-reverse becomes, so just helicopter can both keep a kind of smooth flight posture aloft all the time.
Power Component of the present utility model (motor 17), transmission component (gear cluster) and control assembly (steering wheel 23) all are placed on the frame 24, this textural association mode, promptly simply, stable again, it is also convenient to produce.Two motors 17 are fixed on the framework platform, and dextrorotation power gear 27 and derotation power gear 26 and two motor gears mesh rotation at various height below flat-bed.Utilize two-sided subsides and positioning groove that two steering wheels 23 are placed on the frame on the platform of frame, whole unitized construction is tight, easy for installation.
The advancing, retreat of the utility model aircraft, left and right driftage be by 16 controls of two steering wheels 23 (servo) pulling tilting frame, realizes convenient and practical many of purpose than other the electronic helicopter of the bispin wing by gear motor control cam.
The stabilizing hammer fixed mount with main rotating head be separate, adjustable, can carry out angle changing according to different requirements, satisfied different customers' requirement.
Claims (8)
1. coaxial double-rotary wing RC Goblin, comprise frame, rotor, drive motor, driving gear set and control steering wheel, it is characterized in that: described drive motor and control steering wheel all are assemblied on the framework platform, driving gear set is assemblied in the framework platform below, adopt two ball head connecting rod direct connections between its positive rotor and the tilting frame, adopt L type connecting rod to connect between the derotation wing and the stabilizing hammer.
2. coaxial double-rotary wing RC Goblin as claimed in claim 1 is characterized in that: be fixed with two motors on the described framework platform.
3. coaxial double-rotary wing RC Goblin as claimed in claim 2 is characterized in that: the dextrorotation power gear of described driving gear set and derotation power gear all are located at the transmission that is meshed with two motor gears respectively of framework platform below.
4. coaxial double-rotary wing RC Goblin as claimed in claim 1 is characterized in that: described two control steering wheels become 90 ° to be installed on the framework platform.
5. coaxial double-rotary wing RC Goblin as claimed in claim 4 is characterized in that: two steering wheels of described helicopter are connected with the tilting frame connecting rod respectively.
6. coaxial double-rotary wing RC Goblin as claimed in claim 1 is characterized in that: described rotor employing is combined into rotor and rotor chuck the structure of parts.
7. coaxial double-rotary wing RC Goblin as claimed in claim 6 is characterized in that: the assembly clearance of described rotor and rotating head is: 0.1mm～0.8mm.
8. coaxial double-rotary wing RC Goblin as claimed in claim 1 is characterized in that: two ball head connecting rods of described positive rotor and tilting frame are the two ball head connecting rods of diplopore and become inverted trapezoidal structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420083294 CN2717814Y (en) | 2004-08-23 | 2004-08-23 | Coaxle remote-control double-rotor heligiro |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420083294 CN2717814Y (en) | 2004-08-23 | 2004-08-23 | Coaxle remote-control double-rotor heligiro |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2717814Y true CN2717814Y (en) | 2005-08-17 |
Family
ID=34894016
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200420083294 Expired - Lifetime CN2717814Y (en) | 2004-08-23 | 2004-08-23 | Coaxle remote-control double-rotor heligiro |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2717814Y (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011066708A1 (en) * | 2009-12-04 | 2011-06-09 | Xu Yuehuang | Aerobat toy |
| CN101433766B (en) * | 2007-11-16 | 2012-01-04 | 上海九鹰电子科技有限公司 | Counterbalance system of remote-control model helicopter |
| CN102464107A (en) * | 2010-11-18 | 2012-05-23 | 曹铁生 | Novel theory and method for eliminating buffeting of helicopter wing and increasing flight speed |
| CN101869769B (en) * | 2008-04-21 | 2012-05-23 | 上海九鹰电子科技有限公司 | Mechanical maneuvering system of single-rotor wing model helicopter |
| CN102806994A (en) * | 2011-05-31 | 2012-12-05 | 王略 | Ultra-light single-person deceleration tilting type coaxial helicopter |
| CN103217076A (en) * | 2013-05-07 | 2013-07-24 | 晋西工业集团有限责任公司 | Testing tool of flexibility of rotatable stabilizing devices |
| CN103308272A (en) * | 2013-05-30 | 2013-09-18 | 中国科学院长春光学精密机械与物理研究所 | Non-planar dynamic testing device for aerodynamic performances of dual rotors |
-
2004
- 2004-08-23 CN CN 200420083294 patent/CN2717814Y/en not_active Expired - Lifetime
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101433766B (en) * | 2007-11-16 | 2012-01-04 | 上海九鹰电子科技有限公司 | Counterbalance system of remote-control model helicopter |
| CN101869769B (en) * | 2008-04-21 | 2012-05-23 | 上海九鹰电子科技有限公司 | Mechanical maneuvering system of single-rotor wing model helicopter |
| WO2011066708A1 (en) * | 2009-12-04 | 2011-06-09 | Xu Yuehuang | Aerobat toy |
| CN102464107A (en) * | 2010-11-18 | 2012-05-23 | 曹铁生 | Novel theory and method for eliminating buffeting of helicopter wing and increasing flight speed |
| CN102464107B (en) * | 2010-11-18 | 2014-07-16 | 曹铁生 | Method for eliminating buffeting of helicopter wing and increasing flight speed |
| CN102806994A (en) * | 2011-05-31 | 2012-12-05 | 王略 | Ultra-light single-person deceleration tilting type coaxial helicopter |
| CN103217076A (en) * | 2013-05-07 | 2013-07-24 | 晋西工业集团有限责任公司 | Testing tool of flexibility of rotatable stabilizing devices |
| CN103217076B (en) * | 2013-05-07 | 2015-03-11 | 晋西工业集团有限责任公司 | Testing tool of flexibility of rotatable stabilizing devices |
| CN103308272A (en) * | 2013-05-30 | 2013-09-18 | 中国科学院长春光学精密机械与物理研究所 | Non-planar dynamic testing device for aerodynamic performances of dual rotors |
| CN103308272B (en) * | 2013-05-30 | 2015-12-02 | 中国科学院长春光学精密机械与物理研究所 | A kind of non-planar DCB Specimen aeroperformance dynamic checkout unit |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: SHENZHEN CITY TIANWAITIAN MODEL TRADE CO., LTD. Free format text: FORMER OWNER: SHEN ANPING Effective date: 20061103 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20061103 Address after: 518023, room 938, Wantong building, No. 3002 Sungang East Road, Luohu District, Guangdong, Shenzhen Patentee after: Shenzhen sky sky model Trading Co., Ltd. Address before: 518105 Guangdong city of Shenzhen province Baoan District Songgang Tantou second industrial city second Patentee before: Shen Anping |
|
| ASS | Succession or assignment of patent right |
Owner name: SHEN ANPING Free format text: FORMER OWNER: TIANWAIFEI MODEL TRADING COMPANY LTD., SHENZHEN CITY Effective date: 20081017 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20081017 Address after: Guangdong province Songgang city Shenzhen town Tantou security zone second industrial city second (Feida company), zip code: 518105 Patentee after: Shen Anping Address before: Room 938, Wantong building, No. 3002 Sungang East Road, Luohu District, Guangdong, Shenzhen 518023, China Patentee before: Shenzhen sky fly model Trading Co., Ltd. |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20100827 Address after: 518132, Shenzhen, Guangdong, Baoan District Guangming New ginger habitat education base opposite (side) Patentee after: Shenzhen Shenshi Tongchuang Spaceflight Model Co., Ltd. Address before: 518105 Guangdong province Songgang Tantou town of Shenzhen city security zone second industrial city second (Feida company) Patentee before: Shen Anping |
|
| C17 | Cessation of patent right | ||
| CX01 | Expiry of patent term |
Expiration termination date: 20140823 Granted publication date: 20050817 |