CN204193506U - Break-in control system before and after mould aircraft - Google Patents
Break-in control system before and after mould aircraft Download PDFInfo
- Publication number
- CN204193506U CN204193506U CN201420526960.7U CN201420526960U CN204193506U CN 204193506 U CN204193506 U CN 204193506U CN 201420526960 U CN201420526960 U CN 201420526960U CN 204193506 U CN204193506 U CN 204193506U
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- CN
- China
- Prior art keywords
- break
- mould
- control system
- control
- system before
- 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 provides break-in control system before and after a kind of mould aircraft, comprises steering wheel, steering controller and break-in control lever, and described steering wheel connects steering controller with break-in control lever.Before and after the utility model, course changing control modular construction is simple, turns to regulative mode simple, novel before and after mould aircraft.Be easy to when turning to before and after mould airplane control, turn to sensitive.Can effectively control to make mould airplane reach the object of advance, turning backward.
Description
Technical field
The utility model relates to mould aircraft circles, break-in control system before and after espespecially a kind of mould aircraft.
Background technology
Before and after general mould airplane, course changing control parts are various, particularly have the mould airplane of 3 d function, and front and back course changing control adjustment structure is more complicated, and wayward when turning to before and after regulable control mould aircraft, front and back turn to insensitive.
Summary of the invention
Based on the deficiencies in the prior art, main purpose of the present utility model is to provide that a kind of structure is simple, front and back turn to break-in control system before and after sensitive mould aircraft.
In order to achieve the above object, the utility model provides break-in control system before and after a kind of mould aircraft, comprises steering wheel, steering controller and break-in control lever, and described steering wheel connects steering controller with break-in control lever.
Described steering controller comprises rotating shaft, pitman and tiltler, and described rotating shaft connects tiltler with pitman.Pitman lower end is fixed in described rotating shaft front and back end.The linking arm socket pitman upper end, front and back of described tiltler.Described rotating shaft is fixed on mainboard frame.
Described break-in control lever comprises bow and connecting rod, and described bow two ends are socketed steering wheel and connecting rod respectively.
Described break-in control lever comprises another bow further, and another bow two ends described are socketed rotating shaft and connecting rod respectively.
Compared with prior art, before and after the utility model, break-in Control system architecture is simple, turns to regulative mode simple before and after mould aircraft.Be easy to when turning to before and after mould aircraft control, turn to sensitive.Can effectively control to make mould aircraft reach advance, retreat the sensitive object turned to.
For making the utility model easier to understand, set forth the specific embodiment of break-in control system before and after a kind of mould aircraft of the utility model further below in conjunction with accompanying drawing.
Accompanying drawing explanation
Fig. 1 is the structural representation of break-in control system before and after the utility model mould aircraft.
Fig. 2 is the mounting structure schematic diagram of break-in control system before and after the utility model mould aircraft.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is further described.
Before and after the utility model, break-in control system is installed in the fuselage main body of mould aircraft, forms the front and back break-in control system of mould aircraft.It comprises steering wheel 1, steering controller 2 and break-in control lever 3, and described steering wheel 1 connects steering controller 2 with break-in control lever 3.The work of steering controller 2 is driven by steering wheel 1.
Steering controller 2 comprises rotating shaft 21, pitman 22,23 and tiltler 24, and described rotating shaft 21 connects tiltler 24 with pitman 22,23.Run through with main shaft 4 in the middle part of rotating shaft 21, it is fixed on fuselage mainboard frame upper end.Pitman 22,23 lower end is fixed on status nail 25,26 respectively in rotating shaft 21 front and back end, and the front and back linking arm of tiltler 24 is socketed pitman 22,23 upper end respectively.
Break-in control lever 3 comprises bow 31, bow 32 and connecting rod 33, bow 31 one end is fixed on steering wheel 1 with screw 34, the other end fixes aluminium ball 36 with screw 35, connecting rod 33 is connected again by aluminium ball 36, connecting rod 33 other end connects bow 32 with aluminium ball 37 and screw 38 equally, bow 32 other end is fixed on expenditure part in the middle part of rotating shaft 21 with screw 39, then steering wheel 1 and steering controller 2 are linked up, and drive steering controller 2 to control to turn to before and after mould aircraft by steering wheel 1.
Working method: during startup, driven by motor steering wheel 1 rotates, and then drive rotating shaft 21 to rotate by bow 31, connecting rod 33 and bow 32, rotating shaft 21 pulls tiltler 24 to rotate by pitman 22,23, drive upper screw angle change with tiltler 24 again, then effectively can control the object making mould airplane reach advance, retreat.
The above disclosed preferred embodiment being only the utility model mould aircraft rear steering Control Component, the utility model interest field can not be limited with this, therefore according to the equivalent variations that the utility model claim is done, the scope that the utility model is contained still is belonged to.
Claims (5)
1. a break-in control system before and after mould aircraft, is characterized in that: comprise steering wheel, steering controller and break-in control lever, and described steering wheel connects steering controller with break-in control lever.
2. break-in control system before and after mould aircraft as claimed in claim 1, it is characterized in that: described steering controller comprises rotating shaft, pitman and tiltler, described rotating shaft connects tiltler with pitman.
3. break-in control system before and after mould aircraft as claimed in claim 2, is characterized in that: pitman lower end is fixed in described rotating shaft front and back end.
4. break-in control system before and after mould aircraft as claimed in claim 1, it is characterized in that: described break-in control lever comprises bow and connecting rod, described bow two ends are socketed steering wheel and connecting rod respectively.
5. break-in control system before and after mould aircraft as claimed in claim 4, it is characterized in that: described break-in control lever comprises another bow further, another bow two ends described are socketed rotating shaft and connecting rod respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420526960.7U CN204193506U (en) | 2014-09-12 | 2014-09-12 | Break-in control system before and after mould aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420526960.7U CN204193506U (en) | 2014-09-12 | 2014-09-12 | Break-in control system before and after mould aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204193506U true CN204193506U (en) | 2015-03-11 |
Family
ID=52651507
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420526960.7U Expired - Fee Related CN204193506U (en) | 2014-09-12 | 2014-09-12 | Break-in control system before and after mould aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204193506U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106693394A (en) * | 2015-11-15 | 2017-05-24 | 许美兰 | Model airplane azimuth control system |
-
2014
- 2014-09-12 CN CN201420526960.7U patent/CN204193506U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106693394A (en) * | 2015-11-15 | 2017-05-24 | 许美兰 | Model airplane azimuth control system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150311 Termination date: 20150912 |
|
| EXPY | Termination of patent right or utility model |