CN106606875A - High-maneuvering-performance flight system - Google Patents
High-maneuvering-performance flight system Download PDFInfo
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- CN106606875A CN106606875A CN201510706419.3A CN201510706419A CN106606875A CN 106606875 A CN106606875 A CN 106606875A CN 201510706419 A CN201510706419 A CN 201510706419A CN 106606875 A CN106606875 A CN 106606875A
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- gear
- flight system
- mobility
- axle sleeve
- power source
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Abstract
The invention discloses a high-maneuvering-performance flight system. The high-maneuvering-performance flight system comprises a main body framework, a tail part direction control apparatus, a landing mechanism, a source power mechanism and an integrated remote control apparatus, wherein the source power mechanism comprises a gear speed-reduction clutch mechanism for transferring the power of a power source to a front propeller and a back propeller concurrently. By adoption of the high-maneuvering-performance flight system, one power source can drive two or more propellers to rotate at the same time, so that the weight of the high-maneuvering-performance flight system is greatly reduced, thereby improving the maneuvering performance and the endurance of the high-maneuvering-performance flight system.
Description
Technical field
The present invention relates to a kind of electronic toy, more particularly, the present invention relates to a kind of strong flight system of mobility.
Background technology
As the requirement of people's flight system strong to mobility is improved constantly, often require that the strong flight system of mobility has good flying quality, to increase the interest for manipulating the strong flight system of mobility, it is the weight of the strong flight system of mobility that the flying quality of the flight system strong to mobility is far-reaching, the strong flight system of coaxial double oar mobility is typically all to complete power supply by two power sources, it is also required to two sets of actuating units, this flight system for making mobility strong considerably increases weight, therefore mitigating the weight of the strong flight system of mobility becomes industry urgent problem.
The content of the invention
The technical problem to be solved is provide can mitigate the strong flight system own wt of mobility for the defect existing for above-mentioned prior art, and the strong flight system of the mobility of reduces cost is capable of again.
Solving the technical scheme that adopted of present invention problem is：A kind of strong flight system of mobility includes main body framework, it is connected caudal directions control device with main body framework rear, it is connected to support the landing mechanism of the main body framework with main body framework lower section, the driving source mechanism being arranged in the main body framework and the integrated remote control device that external control signal can be received, described driving source mechanism includes power source, axle sleeve, through the power transmission shaft of the axle sleeve, the front propeller being arranged on power transmission shaft, the rear screw shaft that is arranged on axle sleeve and by the power of described power source while passing to the The gear deceleration clutch of front propeller and rear screw shaft.
The beneficial effects of the present invention is：The power driving source of the strong flight system of mobility passes to front propeller and rear screw shaft simultaneously by The gear deceleration clutch, front propeller and rear screw shaft is set to reversely rotate simultaneously, so make present invention achieves a power source drive pair oars rotation simultaneously, greatly reduces the weight and manufacturing cost of the strong flight system of mobility itself.
As the preferred implementation of the strong flight system of mobility of the present invention, described The gear deceleration clutch includes the power source gear being fixed on power source output shaft, the driving gear on described axle sleeve is engaged and is fixed on the power source gear, the driving gear has planet internal ring gear, at least one planetary gear engaged with driving gear planet internal ring gear, the central gear for engaging with described planetary gear and being fixed on power transmission shaft.
As another preferred implementation of the strong flight system of mobility of the present invention, it also includes dynamic balancer, described dynamic balancer includes gimbal lever's union joint, the gimbal lever and is arranged at the balance weight at gimbal lever two ends, described dynamic balancer is arranged on the upper end of power transmission shaft by gimbal lever's union joint, its whole body is balanced during the strong flight system flight of the dynamic balancer mobility, makes the strong flight system of mobility more can safety and steady flight.
As the strong flight system further embodiment of mobility of the present invention, it also includes steering assembly, described steering assembly includes the pitch being arranged on axle sleeve, steering wheel, the connecting rod of connection steering wheel and pitch, pitch leading truck and is connected the connecting rod of the pitch leading truck and pitch, and the steering assembly efficiently controls the strong flight system of mobility and flexibly turns to.
Below in conjunction with drawings and Examples, technical scheme is described in further detail.
Description of the drawings
Fig. 1 for the strong flight system of mobility of a preferred embodiment of the present invention explosive view.
Specific embodiment
With reference now to Description of Drawings the preferred embodiments of the present invention,.
With reference to Fig. 1, the strong flight system of mobility of the present invention includes the landing mechanism 3 that the caudal directions control device 2 that main body framework 1 and main body framework rear connect and main body framework bottom be connected to support the main body framework, the driving source mechanism 4 being arranged in the main body framework 1, can receive external control signal integrated remote control device 5 and provide the battery 6 of electric energy for consuming parts in main body framework.
Described driving source mechanism 4 includes power source, axle sleeve, the power transmission shaft through the axle sleeve, front propeller, rear screw shaft, power source gear, driving gear, planetary gear, central gear.Front propeller is arranged on power transmission shaft by front vane folder, rear screw shaft is arranged on axle sleeve by rear blade folder, power source gear is installed on described power source output shaft, described driving gear is engaged with power source gear and is fixed on described axle sleeve, driving gear has planet internal ring gear, there are three planetary gears engaged with driving gear planet internal ring gear, described central gear is engaged and is fixed on power transmission shaft with three planetary gears, central gear is provided with planet carrier, and three planetary gear bearings are mutually in 120 degree of positioning planet carriers.Certainly, in other embodiments planetary gear can be one or more.Power transmission shaft lower end is positioned on the bearing block of main body framework by bearing, and axle sleeve upper end is provided with bearing block, and the bearing on power transmission shaft is arranged in bearing block.Power source drive is arranged on the power source gear on power source output shaft, the driving gear that drive is engaged with power source gear, the rotation of driving gear rotates axle sleeve, so that the rear screw shaft rotation being fixed on axle sleeve, and drive three planetary gears engaged with driving gear planet internal ring gear to rotate, three planetary gears rotarily drive central gear rotation, central gear rotation rotates power transmission shaft, so that the front propeller being fixed on power transmission shaft is rotated with the direction contrary with rear screw shaft, it has been achieved in that a power source drives front propeller and rear screw shaft while rotating in the opposite direction simultaneously by gear drive, eliminate a power source and its actuating device, greatly reduce the strong flight system of the mobility weight of itself, so as to improve the flying quality of the strong flight system of mobility and cost-effective.
The strong flight system of the mobility also includes dynamic balancer, the dynamic balancer includes gimbal lever's union joint, the gimbal lever and is arranged at the balance weight at gimbal lever two ends, the gimbal lever is arranged on the upper end of power transmission shaft by gimbal lever's union joint, the dynamic balancer makes to balance its whole body during the strong flight system flight of mobility, make the strong flight system of mobility more can safety and steady flight.
The strong flight system of described mobility also includes steering assembly, the steering assembly includes the pitch being arranged on axle sleeve, steering wheel, the connecting rod of connection steering wheel and pitch, pitch leading truck and is connected the connecting rod of the pitch leading truck and pitch, and the steering assembly efficiently controls model plane and flexibly turns to.
The caudal directions control device includes the tailstock being connected with main body framework, the tail propeller being arranged on tailstock and the tail power source for driving the tail propeller.
Finally should be noted that; above example is only to illustrate technical scheme rather than limiting the scope of the invention; although being explained in detail to the present invention with reference to preferred embodiment; but it will be understood by those within the art that; technical scheme can be modified or equivalent, without deviating from the spirit and scope of technical solution of the present invention.
Claims (6)
1. the strong flight system of a kind of mobility, it is characterised in that：Including main body framework, caudal directions control device, landing mechanism, driving source mechanism and integrated remote control device, the caudal directions control device is connected to the main body framework rear portion, the landing mechanism is connected to below the main body framework, the driving source mechanism and integrated remote control device are arranged on inside the main body framework, described driving source mechanism includes power source, axle sleeve, through the power transmission shaft of the axle sleeve, the front propeller being arranged on power transmission shaft and the rear screw shaft being arranged on axle sleeve, and the power of described power source is passed to into the The gear deceleration clutch of front propeller and rear screw shaft simultaneously.
2. the strong flight system of mobility as claimed in claim 1, it is characterised in that：Described The gear deceleration clutch includes the power source gear being fixed on power source output shaft, the driving gear on described axle sleeve is engaged and is fixed on the power source gear, the driving gear has planet internal ring gear, at least one planetary gear engaged with driving gear planet internal ring gear, the central gear for engaging with described planetary gear and being fixed on power transmission shaft.
3. the strong flight system of mobility as claimed in claim 2, it is characterised in that：Planet carrier is fixed with described central gear, described planetary gear is positioned on the planet carrier.
4. the strong flight system of mobility as claimed in claim 1, it is characterised in that：It also includes dynamic balancer, and described dynamic balancer includes gimbal lever's union joint, the gimbal lever and is arranged at the balance weight at gimbal lever two ends, and described dynamic balancer is arranged on the upper end of power transmission shaft by gimbal lever's union joint.
5. the strong flight system of mobility as claimed in claim 1, it is characterised in that：It also includes steering assembly, and described steering assembly includes the pitch being arranged on axle sleeve, steering wheel, the connecting rod of connection steering wheel and pitch, pitch leading truck and is connected the connecting rod of the pitch leading truck and pitch.
6. the strong flight system of mobility as claimed in claim 1, it is characterised in that：Front propeller folder is additionally provided with described power transmission shaft, described front propeller is clamping on described power transmission shaft by the front propeller, rear screw shaft folder is provided with described axle sleeve, described rear screw shaft is clamping on axle sleeve by the rear screw shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510706419.3A CN106606875A (en) | 2015-10-23 | 2015-10-23 | High-maneuvering-performance flight system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510706419.3A CN106606875A (en) | 2015-10-23 | 2015-10-23 | High-maneuvering-performance flight system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106606875A true CN106606875A (en) | 2017-05-03 |
Family
ID=58614485
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510706419.3A Withdrawn CN106606875A (en) | 2015-10-23 | 2015-10-23 | High-maneuvering-performance flight system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106606875A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201457737U (en) * | 2009-06-29 | 2010-05-12 | 佛山市安尔康姆航拍科技有限公司 | Pusher-type unmanned plane |
| CN202506122U (en) * | 2012-03-17 | 2012-10-31 | 广东奥飞动漫文化股份有限公司 | Remote control toy helicopter capable of bomb dropping control |
| CN203694603U (en) * | 2014-01-16 | 2014-07-09 | 李占超 | Water spraying power remote-control plane |
| CN204355275U (en) * | 2014-08-29 | 2015-05-27 | 深圳市艾特航空科技股份有限公司 | There is the aircraft of safe propulsion system |
| CN106474745A (en) * | 2015-09-01 | 2017-03-08 | 覃道锋 | There is the flight instruments of Remote The gear deceleration clutch system |
-
2015
- 2015-10-23 CN CN201510706419.3A patent/CN106606875A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201457737U (en) * | 2009-06-29 | 2010-05-12 | 佛山市安尔康姆航拍科技有限公司 | Pusher-type unmanned plane |
| CN202506122U (en) * | 2012-03-17 | 2012-10-31 | 广东奥飞动漫文化股份有限公司 | Remote control toy helicopter capable of bomb dropping control |
| CN203694603U (en) * | 2014-01-16 | 2014-07-09 | 李占超 | Water spraying power remote-control plane |
| CN204355275U (en) * | 2014-08-29 | 2015-05-27 | 深圳市艾特航空科技股份有限公司 | There is the aircraft of safe propulsion system |
| CN106474745A (en) * | 2015-09-01 | 2017-03-08 | 覃道锋 | There is the flight instruments of Remote The gear deceleration clutch system |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20170503 |
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| WW01 | Invention patent application withdrawn after publication |