CN105217019A - Unmanned plane horizontal tail wing control mechanism - Google Patents
Unmanned plane horizontal tail wing control mechanism Download PDFInfo
- Publication number
- CN105217019A CN105217019A CN201510685505.0A CN201510685505A CN105217019A CN 105217019 A CN105217019 A CN 105217019A CN 201510685505 A CN201510685505 A CN 201510685505A CN 105217019 A CN105217019 A CN 105217019A
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- China
- Prior art keywords
- horizontal tail
- elevating rudder
- steering wheel
- connecting plate
- connecting rod
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Abstract
A kind of unmanned plane horizontal tail wing control mechanism, is made up of horizontal tail stabilator, horizontal tail steering wheel connecting plate, steering wheel, servo driving axle, connecting rod, bearing pin, horizontal tail elevating rudder, elevating rudder connecting plate, elevating rudder flap; The two ends of horizontal tail stabilator are equipped with steering wheel and bearing pin, the servo driving axle on steering wheel are fixed with horizontal tail steering wheel connecting plate, and the two ends of horizontal tail steering wheel connecting plate are connected to one end of connecting rod, and the other end of connecting rod connects the two ends of elevating rudder connecting plate respectively; The two ends of horizontal tail elevating rudder are respectively equipped with elevating rudder flap, and the interior survey of elevating rudder flap is fixed with elevating rudder connecting plate respectively; Elevating rudder flap is connected with horizontal tail stabilator by bearing pin.Take steering wheel as actuating device, the horizontal tail steering wheel connecting plate be connected with servo driving axle is driven to rotate in the angle set, by connecting rod, the elevating rudder connecting plate that is connected with connecting rod, make horizontal tail elevating rudder take bearing pin as the upper and lower adjustment in axle center, thus realize the lifting controlling unmanned plane.
Description
Technical field
The present invention relates to unmanned plane technical field of aerospace, be specifically related to a kind of novel unmanned plane horizontal tail wing control mechanism.
Background technology
China Patent No. 201420373908.2 discloses a kind of unmanned airplane empennage balance adjusting structure, it comprises tail, the left and right sides of tail upper end are symmetrically installed with two steering wheels respectively, wherein two steering wheels of left surface are steering wheel A and steering wheel B respectively, the two sides of tail lower end are separately installed with tail flank, the lower end of tail flank is connected with balance tail flank by hinge I, the upper side of balance tail flank is provided with base A, base A is hinged with pipe link A, pipe link A one end and base A hinged, the other end is connected with the output shaft of steering wheel A, the upper side of afterbody is provided with empennage, empennage end is connected with balance empennage by hinge II, the left and right sides of balance empennage are symmetrically installed with base respectively, the base that wherein left surface is installed is base B, base B is hinged with pipe link B, pipe link B one end and base B hinged, the other end is connected with the output shaft of steering wheel B.
China Patent No. 201120561911.3 discloses a kind of unmanned airplane empennage installing mechanism of fast demountable, is provided with adapter plate on the top of vertical tail, is provided with L shape draw-in groove at the two ends of adapter plate, is provided with connecting rod in rearward position, vertical tail top; Tailplane is provided with adapter shaft, the lower surface of tailplane is provided with linkage connector, wherein adapter shaft snaps fit onto in L shape draw-in groove, and linkage connector is connected with connecting rod.There is the speed that structure is simple, cheap, safe and reliable, easy to operate, can increase substantially installation exercise.
Summary of the invention
The object of this invention is to provide a kind of unmanned plane horizontal tail wing control mechanism, take steering wheel as actuating device, the horizontal tail steering wheel connecting plate be connected with servo driving axle is driven to rotate in the angle set, by connecting rod, the elevating rudder connecting plate that is connected with connecting rod, make horizontal tail elevating rudder take bearing pin as the upper and lower adjustment in axle center, thus realize the lifting controlling unmanned plane.
For achieving the above object, present invention employs such technical scheme: described unmanned plane horizontal tail wing control mechanism, is made up of horizontal tail stabilator, horizontal tail steering wheel connecting plate, steering wheel, servo driving axle, connecting rod, bearing pin, horizontal tail elevating rudder, elevating rudder connecting plate, elevating rudder flap; It is characterized in that, the two ends of horizontal tail stabilator are equipped with steering wheel and bearing pin, servo driving axle on steering wheel is fixed with horizontal tail steering wheel connecting plate, the two ends of horizontal tail steering wheel connecting plate are connected to one end of connecting rod, and the other end of connecting rod connects the two ends of elevating rudder connecting plate respectively; The two ends of horizontal tail elevating rudder are respectively equipped with elevating rudder flap, and the interior survey of elevating rudder flap is fixed with elevating rudder connecting plate respectively; Elevating rudder flap is connected with horizontal tail stabilator by bearing pin.
After adopting such structure, take steering wheel as actuating device, the horizontal tail steering wheel connecting plate be connected with servo driving axle is driven to rotate in the angle set, by connecting rod, the elevating rudder connecting plate that is connected with connecting rod, make horizontal tail elevating rudder take bearing pin as the upper and lower adjustment in axle center, thus realize the lifting controlling unmanned plane.Good effect of the present invention is: both installed, convenient disassembly, again securely; Reduce air resistance to greatest extent.
Accompanying drawing explanation
Accompanying drawing is depicted as the schematic diagram of concrete structure of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, unmanned plane horizontal tail wing control mechanism of the present invention is described in detail;
As shown in the figure, described unmanned plane horizontal tail wing control mechanism, is made up of horizontal tail stabilator 1, horizontal tail steering wheel connecting plate 2, steering wheel 3, servo driving axle 4, connecting rod 5, bearing pin 6, horizontal tail elevating rudder 7, elevating rudder connecting plate 8, elevating rudder flap 9; It is characterized in that, the two ends of horizontal tail stabilator 1 are equipped with steering wheel 3 and bearing pin 6, servo driving axle 4 on steering wheel 3 is fixed with horizontal tail steering wheel connecting plate 2, the two ends of horizontal tail steering wheel connecting plate 2 are connected to one end of connecting rod 5, and the other end of connecting rod 5 connects the two ends of elevating rudder connecting plate 8 respectively; The two ends of horizontal tail elevating rudder 7 are respectively equipped with elevating rudder flap 9, and the interior survey of elevating rudder flap 9 is fixed with elevating rudder connecting plate 8 respectively; Elevating rudder flap 9 is connected with horizontal tail stabilator 1 by bearing pin 6.
Claims (1)
1. a unmanned plane horizontal tail wing control mechanism, is made up of horizontal tail stabilator (1), horizontal tail steering wheel connecting plate (2), steering wheel (3), servo driving axle (4), connecting rod (5), bearing pin (6), horizontal tail elevating rudder (7), elevating rudder connecting plate (8), elevating rudder flap (9);
It is characterized in that, the two ends of horizontal tail stabilator (1) are equipped with steering wheel (3) and bearing pin (6), servo driving axle (4) on steering wheel (3) is fixed with horizontal tail steering wheel connecting plate (2), the two ends of horizontal tail steering wheel connecting plate (2) are connected to one end of connecting rod (5), and the other end of connecting rod (5) connects the two ends of elevating rudder connecting plate (8) respectively; The two ends of horizontal tail elevating rudder (7) are respectively equipped with elevating rudder flap (9), and the interior survey of elevating rudder flap (9) is fixed with elevating rudder connecting plate (8) respectively; Elevating rudder flap (9) is connected with horizontal tail stabilator (1) by bearing pin (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510685505.0A CN105217019A (en) | 2015-10-16 | 2015-10-16 | Unmanned plane horizontal tail wing control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510685505.0A CN105217019A (en) | 2015-10-16 | 2015-10-16 | Unmanned plane horizontal tail wing control mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105217019A true CN105217019A (en) | 2016-01-06 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510685505.0A Pending CN105217019A (en) | 2015-10-16 | 2015-10-16 | Unmanned plane horizontal tail wing control mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105217019A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018425A (en) * | 2018-08-27 | 2018-12-18 | 成都飞机工业（集团）有限责任公司 | A kind of small drone steering engine exchanging structure of low cost |
| CN113428347A (en) * | 2021-08-17 | 2021-09-24 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle elevator that can dismantle fast |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB645911A (en) * | 1948-05-18 | 1950-11-08 | Saunders Roe Ltd | Improvements in flying controls for aircraft |
| EP0382903A2 (en) * | 1989-02-17 | 1990-08-22 | Dornier Luftfahrt Gmbh | Adjustment device for rudders, in particular for air or water craft |
| CN103057693A (en) * | 2012-12-25 | 2013-04-24 | 天津三爻航空航天科技发展有限公司 | Fixed wing aircraft tail wheel steering apparatus |
| CN205076030U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Unmanned aerial vehicle horizontal tail wing control mechanism |
-
2015
- 2015-10-16 CN CN201510685505.0A patent/CN105217019A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB645911A (en) * | 1948-05-18 | 1950-11-08 | Saunders Roe Ltd | Improvements in flying controls for aircraft |
| EP0382903A2 (en) * | 1989-02-17 | 1990-08-22 | Dornier Luftfahrt Gmbh | Adjustment device for rudders, in particular for air or water craft |
| CN103057693A (en) * | 2012-12-25 | 2013-04-24 | 天津三爻航空航天科技发展有限公司 | Fixed wing aircraft tail wheel steering apparatus |
| CN205076030U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Unmanned aerial vehicle horizontal tail wing control mechanism |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109018425A (en) * | 2018-08-27 | 2018-12-18 | 成都飞机工业（集团）有限责任公司 | A kind of small drone steering engine exchanging structure of low cost |
| CN113428347A (en) * | 2021-08-17 | 2021-09-24 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle elevator that can dismantle fast |
| CN113428347B (en) * | 2021-08-17 | 2022-01-04 | 中国航天空气动力技术研究院 | Unmanned aerial vehicle elevator that can dismantle fast |
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| C06 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160106 |