CN201710968U - Coaxial dual rotor wings helicopter - Google Patents
Coaxial dual rotor wings helicopter Download PDFInfo
- Publication number
- CN201710968U CN201710968U CN2010201592386U CN201020159238U CN201710968U CN 201710968 U CN201710968 U CN 201710968U CN 2010201592386 U CN2010201592386 U CN 2010201592386U CN 201020159238 U CN201020159238 U CN 201020159238U CN 201710968 U CN201710968 U CN 201710968U
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- CN
- China
- Prior art keywords
- thrust unit
- socket axle
- rotary wing
- coaxial double
- rotating 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 relates to an electronic toy field, concretely to a coaxial dual rotor wings helicopter, which includes a motor, a frame, upper and lower rotor wings and a rotating shaft; the lower rotor wing is sleeved on the rotating shaft through a socket shaft in the center; a first pushing apparatus and a second pushing apparatus are arranged on the lower portion of the socket shaft for pushing the socket shaft to make the lower rotor wing incline; and the first pushing apparatus and the second pushing apparatus are disposed at a right angle. The utility model employs the first pushing apparatus and the second pushing apparatus, which are disposed at a right angle, to control the lower rotor wing, thereby the helicopter flies stably, is easy to operate and has low production cost.
Description
Technical field
The utility model relates to the electronic toy field, is specifically related to a kind of coaxial double-rotary wing helicopter.
Background technology
The characteristics of coaxial double-rotary wing helicopter are: two pairs of rotors on same axis, and a pair of is positive rotation, and another offsets the derotation power that produces when two pairs of rotors rotate thus to being despining, and 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.Rotor is made periodic angle of attack variation under the effect of pitch, generation is advanced or retreated therefrom, and the left side is moved or the right side is moved.
Inclinator is the distinctive complexity of helicopter control system and important member, though that its structural form has is multiple, operation principle is basic identical.Inclinator generally is made up of with the revolving part that links to each other with the blade pitch-change-link the not revolving part that links to each other with linkage, and revolving part does not link to each other with revolving part by radial-thrust bearing.Inclinator is by two servomechanism input power, operational ton by the linkage input, convert moving up and down of revolving part and banking motion to through revolving part not, change the blade pitch by the blade pitch-change-link that links to each other with revolving part again, the size and Orientation of blade pulling force is changed, thereby realize the flight control of helicopter.The rotation of inclinator revolving part is driven by the toggle that links to each other with propeller boss, and inclinator structurally will guarantee vertical, horizontal total independence apart from manipulation, therefore turns to mainly and is decided by the inclinator in the steering mechanism.But this inclinator complex structure, the manufacturing cost height, the assembling difficulty is big.
The utility model content
The utility model has overcome shortcoming of the prior art, and a kind of coaxial double-rotary wing helicopter simple and easy, simple in structure of handling is provided, and has improved the flight stability and the handiness of helicopter, and assembling is simple, and manufacturing cost is lower.
In order to solve the problems of the technologies described above, the utility model is achieved through the following technical solutions:
A kind of coaxial double-rotary wing helicopter, comprise motor, frame, rotor and rotating shaft up and down, described rotor down is connected on the rotating shaft by the socket axle sleeve at its center, it is characterized in that: described socket axle bottom is provided with and promotes this socket axle so that first thrust unit and second thrust unit that tilt of rotor down, and above-mentioned first thrust unit and second thrust unit are 90 degree and are provided with.
Further, described first thrust unit is an elliptical ring, and above-mentioned rotating shaft and socket axle pass this elliptical ring, and the both sides of described elliptical ring minor axis are provided with the journal stirrup that connects described frame, and above-mentioned journal stirrup is provided with the chute that first thrust unit is moved along short-axis direction.
Further, described second thrust unit is provided with baffle plate in above-mentioned socket axle both sides, and these second thrust unit two ends are provided with the chute that second thrust unit is moved horizontally.
Further, described socket axle bottom is oval, and this socket axle endoporus top is circular, the ellipse that the bottom of this socket axle endoporus crossfades into downwards for this circle.
Further, the rotor direction has groove under the edge, described socket axle upper circular endoporus both sides.
Further, the described journal stirrup and the second thrust unit side elevation are provided with tenon tooth, and above-mentioned motor is provided with and this tenon tooth meshed gears.
Compared with prior art, the beneficial effects of the utility model are:
1, the utility model adopts first thrust unit and second thrust unit that are 90 degree settings that following rotor is controlled, and has a smooth flight, and easily handles low cost of manufacture.
2, between motor and the thrust unit by gear drive, control more accurate.
Description of drawings
Below in conjunction with the drawings and specific embodiments the utility model is described in further detail.
Fig. 1 is a three-dimensional structure diagram of the present utility model;
Fig. 2 is a three-dimensional decomposition chart of the present utility model;
Fig. 3 is the three-dimensional structure diagram of the utility model socket axle;
Fig. 4 is the upward view of the utility model socket axle;
Fig. 5 is a vertical view of the present utility model;
Fig. 6 be Fig. 5 A-A to cutaway view.
The specific embodiment
As shown in Figure 1, 2, coaxial double-rotary wing helicopter described in the utility model, comprise frame 1, rotor 2,3 and rotating shaft 4 up and down, following rotor 3 is socketed on the rotating shaft 4 by the socket axle 31 at its center, socket axle 31 bottoms are provided with and promote first thrust unit 5 that this socket axle 31 and following rotor 3 swing and second thrust unit, 6, the first thrust units 5 and second thrust unit 6 and be 90 degree settings.
In the present embodiment, first thrust unit, 5 tops are an elliptical ring 51, rotating shaft 4 and socket axle 31 pass elliptical ring 51, the both sides of elliptical ring 51 minor axises are provided with the L shaped journal stirrup 52 that connects frame 1, journal stirrup 52 and frame 1 junction are provided with chute 53, first thrust unit is under the guide effect of chute 53, can move along elliptical ring 51 short-axis directions, second thrust unit 6 is provided with baffle plate 61 in socket axle 31 both sides, second thrust unit, 6 two ends are provided with the chute 62 that second thrust unit 6 is moved horizontally, consult Fig. 3,4, socket axle 31 bottoms are oval, socket axle 31 top endoporus 32 are circular, edge, circular inner hole 32 both sides rotor 3 directions down has groove 33, socket axle endoporus 32 tops are circular, the ellipse 34 that the bottom of socket axle endoporus 32 crossfades into downwards for this circle, because its underpart endoporus is oval, socket axle 31 can swing for the center by rotating shaft 4, be equipped with tenon tooth 7 on journal stirrup 52 and second thrust unit, 6 side elevations, frame 1 is provided with two motors 8, and motor 8 top correspondences are provided with and this tenon tooth 7 meshed gears 81.
Fig. 5 is a vertical view of the present utility model, and the gear 81 of motor 8 and tenon tooth 7 engagements as can be seen from FIG. are to drive first thrust unit 5 or second thrust unit 6 moves.
Fig. 6 be Fig. 5 A-A to cutaway view, socket axle 31 is socketed on the rotating shaft 4, first thrust unit 5 and second thrust unit 6 are positioned at frame 1 top, be provided with cross frame 35 in the socket axle 31, play the effect that connects socket axle 31 and rotating shaft 4, when socket axle 31 swings, socket axle 31 is played the effect of supporting.
The course of work of the present utility model is: when helicopter needs sidesway or forward-reverse, the gear 81 that motor 8 drives its top rotates, the tenon tooth 7 that gear 81 drives journal stirrup 52 1 sides moves first thrust unit 5, the elliptical ring 51 of first thrust unit 5 supports and ends on socket axle 31, rotor certain angle of inclination when 3 rotations under making, thus realize predetermined purpose.When helicopter need be to the opposite direction sidesway, same, the gear 81 that motor 8 drives its top rotated, driving second thrust unit 6 moves, the baffle plate 61 of second thrust unit 6 supports and ends on socket axle 31, and following rotor is the certain angle of inclination when 3 rotations, realizes above-mentioned purpose.
The utility model is not limited to above-mentioned embodiment, if various changes of the present utility model or distortion are not broken away from spirit and scope of the present utility model, if these changes and distortion belong within claim of the present utility model and the equivalent technologies scope, then the utility model also is intended to comprise these changes and distortion.
Claims (6)
1. coaxial double-rotary wing helicopter, comprise motor, frame, rotor and rotating shaft up and down, described rotor down is connected on the rotating shaft by the socket axle sleeve at its center, it is characterized in that: described socket axle bottom is provided with and can promotes this socket axle so that descend first thrust unit and second thrust unit of rotor inclination, and above-mentioned first thrust unit and second thrust unit are 90 degree and are provided with.
2. coaxial double-rotary wing helicopter according to claim 1, it is characterized in that: described first thrust unit is an elliptical ring, above-mentioned rotating shaft and socket axle pass this elliptical ring, the both sides of described elliptical ring minor axis are provided with the journal stirrup that connects described frame, and above-mentioned journal stirrup is provided with the chute that first thrust unit is moved along short-axis direction.
3. coaxial double-rotary wing helicopter according to claim 1 is characterized in that: described second thrust unit is provided with baffle plate in above-mentioned socket axle both sides, and these second thrust unit two ends are provided with the chute that second thrust unit is moved horizontally.
4. according to each described coaxial double-rotary wing helicopter of claim 1 to 3, it is characterized in that: described socket axle bottom is for oval, and this socket axle endoporus top is circular, the ellipse that the bottom of this socket axle endoporus crossfades into downwards for this circle.
5. coaxial double-rotary wing helicopter according to claim 4 is characterized in that: described socket axle upper end circular inner hole has groove to both sides.
6. coaxial double-rotary wing helicopter according to claim 5 is characterized in that: the described journal stirrup and the second thrust unit side elevation are provided with tenon tooth, and above-mentioned motor is provided with and this tenon tooth meshed gears.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201592386U CN201710968U (en) | 2010-04-12 | 2010-04-12 | Coaxial dual rotor wings helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201592386U CN201710968U (en) | 2010-04-12 | 2010-04-12 | Coaxial dual rotor wings helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201710968U true CN201710968U (en) | 2011-01-19 |
Family
ID=43456963
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201592386U Expired - Fee Related CN201710968U (en) | 2010-04-12 | 2010-04-12 | Coaxial dual rotor wings helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201710968U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013004010A1 (en) * | 2011-07-04 | 2013-01-10 | 深圳市子轩玩具有限公司 | Multifunctional toy aircraft |
| CN105818978A (en) * | 2016-03-30 | 2016-08-03 | 广东飞轮科技股份有限公司 | Double-wing aircraft with improved direction control mechanism |
-
2010
- 2010-04-12 CN CN2010201592386U patent/CN201710968U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013004010A1 (en) * | 2011-07-04 | 2013-01-10 | 深圳市子轩玩具有限公司 | Multifunctional toy aircraft |
| CN105818978A (en) * | 2016-03-30 | 2016-08-03 | 广东飞轮科技股份有限公司 | Double-wing aircraft with improved direction control mechanism |
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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: 20110119 Termination date: 20130412 |