CN105015762A - Aircraft geared trim tab mechanism with variable transmission ratio - Google Patents
Aircraft geared trim tab mechanism with variable transmission ratio Download PDFInfo
- Publication number
- CN105015762A CN105015762A CN201410160565.6A CN201410160565A CN105015762A CN 105015762 A CN105015762 A CN 105015762A CN 201410160565 A CN201410160565 A CN 201410160565A CN 105015762 A CN105015762 A CN 105015762A
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- slide rail
- aircraft
- guide pin
- pin bushing
- rail guide
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Abstract
The invention provides an aircraft geared trim tab mechanism with a variable transmission ratio. The aircraft geared trim tab mechanism comprises a first fixed sliding rail support, a first sliding rail guide sleeve, a connecting rocker arm, an adjustable pull rod, a second fixed sliding rail support, a second sliding rail guide sleeve, a trim tab pull rod, a geared trim tab and a rudder surface.
Description
Technical field
The present invention relates to flight control method.
Background technology
Rudder face servo tab during existing Aircraft Flight Test is all according to a fixing transmitting ratio design, cannot adjust accordingly according to flight reflection.The version of prior art as shown in Figure 1.
Existing aircraft servo tab is all according to the design of fixing transmitting ratio, all the time the ratio becoming to fix with rudder face along with the deflection servo tab of rudder face deflects, but this design makes the aircraft stick force of pure mechanical manoeuvring system cannot realize a linear growth ratio, the operation stick force of aviator can not increase and linear increase along with control surface deflection, has a smooth area.
Summary of the invention
The technical problem to be solved in the present invention:
Patent of the present invention achieves the change of transmitting ratio in the process deflected of aircraft servo tab and rudder face, make servo tab along with the increase of rudder face aperture, the transmitting ratio of servo tab and rudder face aperture is progressively changing, and finally makes the aircraft stick force of depositing mechanical manoeuvring system realize a linear change.
Technical scheme of the present invention:
A kind of aircraft servo tab mechanism of variable ratio, it is characterized in that, comprise the first fixed rack bearing, first slide rail guide pin bushing, connecting rocker arm, adjustable rod, second fixed rack bearing, second slide rail guide pin bushing, tab pull bar, servo tab and rudder face, first fixed rack bearing and the second fixed rack bearing are fixed on aircraft stabilator, first slide rail guide pin bushing is installed on the slide rail of the first fixed rack bearing, second slide rail guide pin bushing is installed on the slide rail of the second fixed rack bearing, first slide rail guide pin bushing lower end and connecting rocker arm one end hinged, the connecting rocker arm other end and aircraft rudder surface hinged, upper end and the adjustable rod of the first slide rail guide pin bushing are hinged, the other end of adjustable rod and the second slide rail guide pin bushing upper end thereof, second slide rail guide pin bushing lower end and tab pull bar one end hinged, the other end and the servo tab of tab pull bar are hinged.
Patent of the present invention is that the stick force in order to meet pure mechanical manoeuvring system aircraft requires needs, the transmitting ratio of aircraft servo tab and rudder face is designed to variable ratio mechanism, make servo tab along with the increase of rudder face aperture, the transmitting ratio of servo tab and rudder face aperture is progressively changing, and finally makes the aircraft stick force of pure mechanical manoeuvring system realize a linear change.Patent of the present invention does not need complicated parts, and safety simultaneously, reliability are high.
Beneficial effect of the present invention:
The present invention is widely used in aircraft rudder surface servo tab system, can meet at structure space smaller, realizes the servo tab deflection of variable-speed ratio.
Accompanying drawing explanation
Fig. 1 existing aircraft servo tab steering unit schematic diagram;
Fig. 2 variable ratio aircraft servo tab structural scheme of mechanism;
Detailed description of the invention
A kind of aircraft servo tab mechanism of variable ratio, it is characterized in that, comprise the first fixed rack bearing 1, first slide rail guide pin bushing 2, connecting rocker arm 3, adjustable rod 4, second fixed rack bearing 6, second slide rail guide pin bushing 5, tab pull bar 7, rudder face 8, servo tab 9, first fixed rack bearing 1 and the second fixed rack bearing 6 are fixed on aircraft stabilator, first slide rail guide pin bushing 2 is installed on the slide rail of the first fixed rack bearing 1, second slide rail guide pin bushing 5 is installed on the slide rail of the second fixed rack bearing 6, first slide rail guide pin bushing 2 lower end and connecting rocker arm 3 one end hinged, connecting rocker arm 3 other end and aircraft rudder surface 8 hinged, upper end and the adjustable rod 4 of the first slide rail guide pin bushing 2 are hinged, the other end of adjustable rod 4 and the upper end thereof of the second slide rail guide pin bushing 5, lower end and tab pull bar 7 one end of second slide rail guide pin bushing 5 are hinged, the other end and the servo tab 9 of tab pull bar 7 are hinged.
When aircraft rudder surface 8 moves, first fixed rack bearing 1 and the second fixed rack bearing 6 are fixed, aircraft rudder surface 8 drives the first slide rail guide pin bushing 2 to slide at the first fixed rack bearing 1 by connecting rocker arm 3, driven motion on the second fixed rack bearing 6 by the first slide rail guide pin bushing 2 by adjustable rod 4 while of second slide rail guide pin bushing 5, while the second slide rail guide pin bushing 5 moves, drive servo tab 9 to deflect accordingly.
Due to the motion of the second slide rail guide pin bushing 5 on the second fixed rack bearing 6, the distance between itself and the pivot point of aircraft rudder surface 8 is caused to change, thus former fixing aircraft servo tab four-bar linkage has been changed into the four-bar linkage becoming rocking arm radius, achieve servo tab variable ratio mechanism.
Effect of the present invention is: 1) provide a kind of variable ratio aircraft servo tab mechanism; 2) less structural weight loss; 3) relatively little installing space; 4) manufacture, assembly technology is simple; 5) variable ratio is realized; 6) easy to use, cost is low; 6) reliability is high.
Claims (1)
1. the aircraft servo tab mechanism of a variable ratio, it is characterized in that, comprise the first fixed rack bearing, first slide rail guide pin bushing, connecting rocker arm, adjustable rod, second fixed rack bearing, second slide rail guide pin bushing, tab pull bar, servo tab and rudder face, first fixed rack bearing and the second fixed rack bearing are fixed on aircraft stabilator, first slide rail guide pin bushing is installed on the slide rail of the first fixed rack bearing, second slide rail guide pin bushing is installed on the slide rail of the second fixed rack bearing, first slide rail guide pin bushing lower end and connecting rocker arm one end hinged, the connecting rocker arm other end and aircraft rudder surface hinged, upper end and the adjustable rod of the first slide rail guide pin bushing are hinged, the other end of adjustable rod and the second slide rail guide pin bushing upper end thereof, second slide rail guide pin bushing lower end and tab pull bar one end hinged, the other end and the servo tab of tab pull bar are hinged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410160565.6A CN105015762B (en) | 2014-04-21 | 2014-04-21 | A kind of aircraft servo tab mechanism of variable ratio |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410160565.6A CN105015762B (en) | 2014-04-21 | 2014-04-21 | A kind of aircraft servo tab mechanism of variable ratio |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105015762A true CN105015762A (en) | 2015-11-04 |
| CN105015762B CN105015762B (en) | 2016-12-07 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410160565.6A Active CN105015762B (en) | 2014-04-21 | 2014-04-21 | A kind of aircraft servo tab mechanism of variable ratio |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105015762B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108408026A (en) * | 2018-05-16 | 2018-08-17 | 江西冠通用飞机有限公司 | A kind of general-purpose aircraft tailspin changes device |
| CN109484665A (en) * | 2018-12-14 | 2019-03-19 | 中航沈飞民用飞机有限责任公司 | A kind of half free regulating mechanism in blocking type hatch door course |
| CN109592012A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of general-purpose aircraft composite material rudder having trimmer and manufacturing method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CS220148B1 (en) * | 1981-11-04 | 1983-03-25 | Jaroslav Dostal | Two-slit flap extending mechanism |
| US6257528B1 (en) * | 1999-07-20 | 2001-07-10 | The Boeing Company | Vehicle control system and method employing control surface and geared tab |
| CN201597752U (en) * | 2010-02-08 | 2010-10-06 | 哈尔滨飞机工业集团有限责任公司 | Follower of aircraft elevator tab |
| CN101959754A (en) * | 2007-08-06 | 2011-01-26 | 空中客车营运有限公司 | High lift system for an aircraft |
| CN102105355A (en) * | 2008-07-23 | 2011-06-22 | 空客运营有限公司 | Aircraft control surface |
| CN102574574A (en) * | 2009-09-03 | 2012-07-11 | 空中客车运营有限公司 | Adjusting mechanism for kinematically guiding an adjusting body during displacement on a supporting structural part, adjusting mechanism for kinematically adjusting a vertically lifting body and vertical lift system comprising said type of adjusting |
-
2014
- 2014-04-21 CN CN201410160565.6A patent/CN105015762B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CS220148B1 (en) * | 1981-11-04 | 1983-03-25 | Jaroslav Dostal | Two-slit flap extending mechanism |
| US6257528B1 (en) * | 1999-07-20 | 2001-07-10 | The Boeing Company | Vehicle control system and method employing control surface and geared tab |
| CN101959754A (en) * | 2007-08-06 | 2011-01-26 | 空中客车营运有限公司 | High lift system for an aircraft |
| CN102105355A (en) * | 2008-07-23 | 2011-06-22 | 空客运营有限公司 | Aircraft control surface |
| CN102574574A (en) * | 2009-09-03 | 2012-07-11 | 空中客车运营有限公司 | Adjusting mechanism for kinematically guiding an adjusting body during displacement on a supporting structural part, adjusting mechanism for kinematically adjusting a vertically lifting body and vertical lift system comprising said type of adjusting |
| CN201597752U (en) * | 2010-02-08 | 2010-10-06 | 哈尔滨飞机工业集团有限责任公司 | Follower of aircraft elevator tab |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108408026A (en) * | 2018-05-16 | 2018-08-17 | 江西冠通用飞机有限公司 | A kind of general-purpose aircraft tailspin changes device |
| CN109592012A (en) * | 2018-11-02 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of general-purpose aircraft composite material rudder having trimmer and manufacturing method |
| CN109484665A (en) * | 2018-12-14 | 2019-03-19 | 中航沈飞民用飞机有限责任公司 | A kind of half free regulating mechanism in blocking type hatch door course |
| CN109484665B (en) * | 2018-12-14 | 2021-09-21 | 中航沈飞民用飞机有限责任公司 | Half-blocking cabin door course free adjusting mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105015762B (en) | 2016-12-07 |
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Effective date of registration: 20180511 Address after: 150066 No. 15, Friendship Association street, Ping Fang District, Harbin, Heilongjiang. Patentee after: Harbin general aircraft industry limited liability company Address before: 150066 No. 15, Friendship Association street, Ping Fang District, Harbin, Heilongjiang. Patentee before: Harbin Aircraft Industrial (Group) Co., Ltd. |
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| TR01 | Transfer of patent right |