CN106031830A - Aircraft capable of effectively improving endurance - Google Patents
Aircraft capable of effectively improving endurance Download PDFInfo
- Publication number
- CN106031830A CN106031830A CN201510181508.0A CN201510181508A CN106031830A CN 106031830 A CN106031830 A CN 106031830A CN 201510181508 A CN201510181508 A CN 201510181508A CN 106031830 A CN106031830 A CN 106031830A
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- Prior art keywords
- power
- gear wheel
- aircraft
- power set
- effectively improved
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Abstract
The invention provides an aircraft capable of effectively improving the endurance. The aircraft includes a first power device, a second power device, and a transmission shaft, and the first power device and the second power device are connected through the transmission shaft. Such a remote control aircraft toy greatly simplifies the integral structure of a model aircraft, but also reduces the weight of the fuselage, thereby effectively reducing the energy consumption and prolonging the flight time.
Description
Technical field
The present invention relates to model plane field, a kind of aircraft that can be effectively improved flying power.
Background technology
General aeromodelling airplane is by belt transmission or gear drive driving the rotation of whole steering mechanism, and in belt transmission, the long-term friction use due to belt causes bigger abrasion so that whole steering mechanism is insensitive；And gear-driven Power Component is made up of several gears, wherein, two master gears of equal diameters are parallel superimposedly run through main shaft and with axle synchronous axial system, one of them master gear drives and the propeller unit synchronous axial system being installed on main shaft, and the gear of end part of driving shaft is meshed with another one master gear, drives empennage steering unit and axle synchronous axial system by gear wheel, so, making airframe structure complex, and add the overall weight of fuselage, weight increases will increase energy consumption.
In view of this, it is desirable to provide the Power Component of a kind of aeromodelling airplane that can simplify airframe structure.
Summary of the invention
Content
Based on the deficiencies in the prior art, present invention is primarily targeted at a kind of aircraft that can be effectively improved flying power that disclosure satisfy that flying for long time of offer.
In order to achieve the above object, the invention provides a kind of aircraft that can be effectively improved flying power, including the first power set, the second power set and power transmission shaft, the first power set and the second power set are connected by power transmission shaft, first power set include main shaft, gear train and fixed cover, gear train includes concentric locking collar motor gear wheel on main shaft and turns to gear wheel, offers circular groove, turn to gear wheel to be built in this groove in the middle part of motor gear wheel；Described second power set include caudal wing shaft and are enclosed within empennage tooth sector thereon and empennage turning sleeve；The both ends of described power transmission shaft are respectively provided with drive pinion；The drive pinion of described end part of driving shaft is meshed with the empennage tooth sector turning to gear wheel and the second power set of the first power set respectively.
It is cased with tailing axle fixture on caudal wing shaft further, by tailing axle fixture, empennage tooth sector is positioned.Tail pipe also it is cased with outside power transmission shaft.Also being cased with collar bush outside main shaft, described unilateral bearing is closely set on collar bush.
Compared with prior art, in the present invention, unilateral bearing, turn to gear wheel and gear wheel axle sleeve to connect to be fixed as one, make it appear to as a single motor gear wheel, the fixed form of this gear assembled structure not only novel appearance, uniqueness, and enormously simplify the overall structure of aeromodelling airplane, also mitigate the weight of fuselage, effectively reduce energy consumption, extend the flight time.Additionally; dispose unilateral bearing; for a further feature of the present disclosure; it forces aeromodelling airplane to rotate in one direction; this flight control method makes model helicopter motor when running into flight and being unexpected will not exhaust electric power because of opposing propeller reverse resistance at once and quit work; aeromodelling airplane can slowly be declined, air crash loss is preferably minimized, fuselage is played a protective role.
For making the present invention easier to understand, the specific embodiment of the present invention a kind of aircraft that can be effectively improved flying power is expanded on further below in conjunction with accompanying drawing.
Accompanying drawing explanation
Fig. 1 is the structural representation that the present invention can be effectively improved the aircraft of flying power.
Detailed description of the invention
Below in conjunction with the accompanying drawings, the present invention will be further described.
With reference to shown in Fig. 1, Power Component 100 of the present invention is installed on the middle part of model plane, and its one end connects steering unit, and the other end connects tail steering set, drives steering unit and tail steering set synchronous axial system by the transmission of Power Component.
This aircraft that can be effectively improved flying power includes the first power set the 1, second power set 2 and power transmission shaft 3, connects the first power set 1 and the second power set 2 by power transmission shaft 3.Wherein, first power set 1 include main shaft 10, gear train 11 and fixed cover 12, main shaft 10 is outer is also cased with collar bush 101, gear train 11 includes motor gear wheel 110 and turns to gear wheel 112, and on the panel of motor gear wheel 110, symmetry has several holes, to alleviate its weight, circular groove 110a is offered in the middle part of it, turning to gear wheel 112 to be built in the groove 110a of motor gear wheel 110, turn to the flank of tooth 112 ' of gear wheel 112 to be upwards distributed, this flank of tooth 112 ' is substantially vertical with main shaft 10.Fixed cover 12 includes gear wheel axle sleeve 120 and the unilateral bearing 122 running through main shaft 10 with one heart, unilateral bearing 122 is embedded in gear wheel axle sleeve 120 and banding is in the middle part of main shaft 10, gear wheel 112 and motor gear wheel 110 fixed cover will be turned at the middle part of main shaft 10 by unilateral bearing 122 and gear wheel axle sleeve 120.
Second power set 2 include caudal wing shaft 20 and are enclosed within empennage tooth sector 22 thereon, empennage turning sleeve 24, tailing axle fixture 26, are positioned by empennage tooth sector 22 by tailing axle fixture 26.
The both ends of power transmission shaft 3 are respectively provided with two drive pinions 30.In one embodiment of the invention, power transmission shaft 3 is outer is cased with tail pipe 32 the most further.The drive pinion 30 of power transmission shaft 3 end is meshed with the empennage tooth sector 22 turning to gear wheel 112 and the second power set 2 respectively, so, power transmission shaft 3 itself can be followed and be turned to gear wheel 112 to rotate together, and, driven the rotation of the second power set 2 by the transmission between gear, thus drive the synchronous rotary of whole steering mechanism and tail steering set.
Described embodiment is the present invention preferably embodiment; but do not represent and be only limited by the examples; any change done in the case of other any spirit without departing from the present invention and principle, modify, substitute, combine, simplify; it is regarded as and the substitute mode of present invention equivalence, within being all contained in protection scope of the present invention.
Claims (5)
1. the aircraft that can be effectively improved flying power, it is characterized in that: include the first power set, the second power set and power transmission shaft, the first power set and the second power set are connected by power transmission shaft, first power set include main shaft, gear train and fixed cover, gear train includes concentric locking collar motor gear wheel on main shaft and turns to gear wheel, offer circular groove in the middle part of motor gear wheel, turn to gear wheel to be built in this groove；Described second power set include caudal wing shaft and are enclosed within empennage tooth sector thereon and empennage turning sleeve；The both ends of described power transmission shaft are respectively provided with drive pinion；The drive pinion of described end part of driving shaft is meshed with the empennage tooth sector turning to gear wheel and the second power set of the first power set respectively.
The aircraft of flying power can be effectively improved the most as claimed in claim 1, it is characterised in that: farther include to be embedded in the unilateral bearing of gear wheel axle sleeve.
The aircraft of flying power can be effectively improved the most as claimed in claim 2, it is characterised in that the flank of tooth turning to gear wheel described in: is vertical with main shaft.
The aircraft of flying power can be effectively improved the most as claimed in claim 3, it is characterised in that: being also cased with collar bush outside described main shaft, described unilateral bearing is closely set on collar bush.
The aircraft of flying power can be effectively improved the most as claimed in claim 4, it is characterised in that: it is cased with tailing axle fixture on described caudal wing shaft further, by tailing axle fixture, empennage tooth sector is positioned.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510181508.0A CN106031830A (en) | 2015-04-16 | 2015-04-16 | Aircraft capable of effectively improving endurance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510181508.0A CN106031830A (en) | 2015-04-16 | 2015-04-16 | Aircraft capable of effectively improving endurance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106031830A true CN106031830A (en) | 2016-10-19 |
Family
ID=57148920
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510181508.0A Pending CN106031830A (en) | 2015-04-16 | 2015-04-16 | Aircraft capable of effectively improving endurance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106031830A (en) |
-
2015
- 2015-04-16 CN CN201510181508.0A patent/CN106031830A/en active Pending
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20161019 |