CN106466528A - Rotor blade, rotor, aircraft and method - Google Patents
Rotor blade, rotor, aircraft and method Download PDFInfo
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- CN106466528A CN106466528A CN201510518379.XA CN201510518379A CN106466528A CN 106466528 A CN106466528 A CN 106466528A CN 201510518379 A CN201510518379 A CN 201510518379A CN 106466528 A CN106466528 A CN 106466528A
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- axle sleeve
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Abstract
The invention discloses a kind of rotor blade, rotor, aircraft and method, including main body framework, caudal directions control device, landing mechanism, driving source mechanism and integrated remote control device, in described driving source mechanism, include the The gear deceleration clutch that the power of described power source is passed to simultaneously front propeller and rear screw shaft；Present invention achieves a power source drives double oars or many oars to rotate simultaneously, greatly reduce rotor blade, rotor, the aircraft and method weight of itself, thus improve mobility and the endurance of rotor blade, rotor, aircraft and method.
Description
Technical field
The present invention relates to a kind of electronic toy, more particularly, the present invention relates to a kind of rotor blade, rotor, aircraft and method.
Background technology
With people to rotor blade, rotor, the requirement of aircraft and method improves constantly, often require that rotor blade, rotor, aircraft and method have good flying quality, manipulate rotor blade to increase, rotor, aircraft and the interest of method, to rotor blade, rotor, the flying quality of aircraft and method is far-reaching to be rotor blade, rotor, aircraft and the weight of method, coaxially double oar rotor blades, rotor, aircraft and method are typically all to complete power supply by two power sources, it is also required to two sets of actuating units, this makes rotor blade, rotor, aircraft and method considerably increase weight, therefore mitigate rotor blade, rotor, the weight of aircraft and method becomes industry urgent problem.
Content of the invention
The technical problem to be solved is provide can mitigate rotor blade, rotor, aircraft and method own wt for the defect existing for above-mentioned prior art, is capable of rotor blade, rotor, aircraft and the method for reduces cost again.
Solve present invention problem be employed technical scheme comprise that：A kind of rotor blade, rotor, aircraft and method include main body framework, it is connected caudal directions control device with main body framework rear, with be connected to support the landing mechanism of this main body framework below main body framework, the driving source mechanism being arranged in described 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, run through the power transmission shaft of this axle sleeve, it is arranged at the front propeller on power transmission shaft, the rear screw shaft being arranged on axle sleeve and the The gear deceleration clutch that the power of described power source is passed to simultaneously front propeller and rear screw shaft.
The beneficial effects of the present invention is：The power driving source of rotor blade, rotor, aircraft and method passes to front propeller and rear screw shaft by The gear deceleration clutch simultaneously, so that front propeller and rear screw shaft is reversely rotated simultaneously, so make, present invention achieves a power source drives double oars to rotate simultaneously, to greatly reduce the weight Manufacturing cost of rotor blade, rotor, aircraft and method itself.
Preferred implementation as rotor blade of the present invention, rotor, aircraft and method, described The gear deceleration clutch includes the power source gear being fixed on power source output shaft, engage and be fixed on the driving gear on described axle sleeve with this power source gear, this driving gear has planet internal ring gear, at least one planetary gear being engaged with driving gear planet internal ring gear, is engaged with described planetary gear and is fixed on the central gear on power transmission shaft.
As rotor blade of the present invention, rotor, aircraft and another preferred implementation of method, it also includes dynamic balancer, the balance weight that described dynamic balancer includes gimbal lever's union joint, the gimbal lever and is arranged at gimbal lever two ends, described dynamic balancer is arranged on the upper end of power transmission shaft by gimbal lever's union joint, balance its whole body when this dynamic balancer rotor blade, rotor, aircraft and method flight, so that rotor blade, rotor, aircraft and method more can safety and steady be flown.
As rotor blade of the present invention, rotor, aircraft and method further embodiment, it also includes steering assembly, pitch that described steering assembly includes being arranged on axle sleeve, steering wheel, the connecting rod connecting steering wheel and pitch, pitch leading truck and the connecting rod being connected this pitch leading truck and pitch, this steering assembly efficiently controls rotor blade, rotor, aircraft and method and flexibly turns to.
Below in conjunction with drawings and Examples, technical scheme is described in further detail.
Brief description
Fig. 1 is the rotor blade of a preferred embodiment of the present invention, the explosive view of rotor, aircraft and method.
Specific embodiment
With reference now to Description of Drawings the preferred embodiments of the present invention,.
With reference to Fig. 1, rotor blade of the present invention, rotor, aircraft and method include caudal directions control device 2 that main body framework 1 is connected with main body framework rear and main body framework bottom is connected to support the landing mechanism 3 of this main body framework, the driving source mechanism 4 being arranged in described main body framework 1, can receive external control signal integrated remote control device 5 and be arranged on the battery 6 for consuming parts offer electric energy in main body framework.
Described driving source mechanism 4 includes power source, axle sleeve, the power transmission shaft running through this 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, on described power source output shaft, power source gear is installed, 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 engaging with driving gear planet internal ring gear, described central gear is engaged with three planetary gears and is fixed on power transmission shaft, central gear is provided with planet carrier, and three planetary gear bearings are mutually in 120 degree of positioning planet carriers.Certainly, planetary gear can be one or more in other embodiments.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，Drive the driving gear engaging with power source gear，The rotation of driving gear makes axle sleeve rotate，So that the rear screw shaft rotation being fixed on axle sleeve，And drive the three planetary gear rotations engaged with driving gear planet internal ring gear，Three planetary gears rotarily drive central gear rotation，Central gear rotation makes power transmission shaft rotate，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 to rotate in the opposite direction by gear drive simultaneously simultaneously，Eliminate a power source and its actuating device，Greatly reduce rotor blade、Rotor、Aircraft and the weight of method itself，Thus improve rotor blade、Rotor、The flying quality of aircraft and method and cost-effective.
Described rotor blade, rotor, aircraft and method also include dynamic balancer, the balance weight that this dynamic balancer includes gimbal lever's union joint, the gimbal lever and is arranged at gimbal lever two ends, the gimbal lever is arranged on the upper end of power transmission shaft by gimbal lever's union joint, this dynamic balancer makes to balance its whole body when rotor blade, rotor, aircraft and method flight, so that rotor blade, rotor, aircraft and method more can safety and steady be flown.
Described rotor blade, rotor, aircraft and method also include steering assembly, pitch that this steering assembly includes being arranged on axle sleeve, steering wheel, the connecting rod connecting steering wheel and pitch, pitch leading truck and the connecting rod being connected this pitch leading truck and pitch, this steering assembly efficiently controls model plane and flexibly turns to.
Described 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 driving this tail propeller.
Finally be should be noted that; above example is only in order 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 (7)
1. a kind of rotor blade, rotor, aircraft and method it is characterised in that：Including main body framework, caudal directions control device, landing mechanism, driving source mechanism and integrated remote control device, described caudal directions control device is connected to described main body framework rear portion, described landing mechanism is connected to below described main body framework, described driving source mechanism and integrated remote control device are arranged on inside described main body framework, described driving source mechanism includes power source, axle sleeve, run through the power transmission shaft of this axle sleeve, the front propeller that is arranged on power transmission shaft and be arranged at the rear screw shaft on axle sleeve, and the power of described power source is passed to simultaneously the The gear deceleration clutch of front propeller and rear screw shaft.
2. rotor blade as claimed in claim 1, rotor, aircraft and method it is characterised in that：Described The gear deceleration clutch includes the power source gear being fixed on power source output shaft, engage and be fixed on the driving gear on described axle sleeve with this power source gear, this driving gear has planet internal ring gear, at least one planetary gear being engaged with driving gear planet internal ring gear, is engaged with described planetary gear and is fixed on the central gear on power transmission shaft.
3. rotor blade as claimed in claim 2, rotor, aircraft and method it is characterised in that：Planet carrier is fixed with described central gear, described planetary gear is positioned on this planet carrier.
4. rotor blade as claimed in claim 1, rotor, aircraft and method it is characterised in that：It also includes dynamic balancer, the balance weight that described dynamic balancer includes gimbal lever's union joint, the gimbal lever and is arranged 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. rotor blade as claimed in claim 1, rotor, aircraft and method it is characterised in that：It also includes steering assembly, pitch that described steering assembly includes being arranged on axle sleeve, steering wheel, the connecting rod connecting steering wheel and pitch, pitch leading truck and the connecting rod being connected this pitch leading truck and pitch.
6. rotor blade as claimed in claim 1, rotor, aircraft and method it is characterised in that：Front propeller folder is additionally provided with described power transmission shaft, described front propeller passes through that this front propeller is clamping to be provided with rear screw shaft folder on described power transmission shaft on described axle sleeve, described rear screw shaft pass through this rear screw shaft clamping on axle sleeve.
7. rotor blade as claimed in claim 1, rotor, aircraft and method it is characterised in that：Described hollow pipe top is provided with bearing block, and described power transmission shaft top is additionally provided with the bearing being placed in hollow pipe upper axis bearing, and lower end is provided with the positioning bearing being placed in main body framework bearing block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510518379.XA CN106466528A (en) | 2015-08-21 | 2015-08-21 | Rotor blade, rotor, aircraft and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510518379.XA CN106466528A (en) | 2015-08-21 | 2015-08-21 | Rotor blade, rotor, aircraft and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106466528A true CN106466528A (en) | 2017-03-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510518379.XA Pending CN106466528A (en) | 2015-08-21 | 2015-08-21 | Rotor blade, rotor, aircraft and method |
Country Status (1)
| Country | Link |
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| CN (1) | CN106466528A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106540459A (en) * | 2015-09-20 | 2017-03-29 | 许美兰 | Rotor blade, rotor, aircraft and method |
| CN106552433A (en) * | 2015-09-25 | 2017-04-05 | 郑华耀 | Intelligent model plane |
| CN106552425A (en) * | 2015-09-25 | 2017-04-05 | 郑华耀 | Aerial device with multiple propulsion systems |
-
2015
- 2015-08-21 CN CN201510518379.XA patent/CN106466528A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106540459A (en) * | 2015-09-20 | 2017-03-29 | 许美兰 | Rotor blade, rotor, aircraft and method |
| CN106552433A (en) * | 2015-09-25 | 2017-04-05 | 郑华耀 | Intelligent model plane |
| CN106552425A (en) * | 2015-09-25 | 2017-04-05 | 郑华耀 | Aerial device with multiple propulsion systems |
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| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
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Application publication date: 20170301 |