CN103171761B - A kind of device preventing front-wheel shimmy of airplane - Google Patents
A kind of device preventing front-wheel shimmy of airplane Download PDFInfo
- Publication number
- CN103171761B CN103171761B CN201310126716.1A CN201310126716A CN103171761B CN 103171761 B CN103171761 B CN 103171761B CN 201310126716 A CN201310126716 A CN 201310126716A CN 103171761 B CN103171761 B CN 103171761B
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- wear ring
- shimmy
- wheel
- clip
- airplane
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- Fluid-Damping Devices (AREA)
- Vibration Dampers (AREA)
Abstract
The present invention provides a kind of device preventing front-wheel shimmy of airplane, and it includes being set on aircraft nose wheel pillar and be provided with the wear ring of opening, is set in clip outside described wear ring, is sheathed on described clip opening and by the bolt assembly of wear ring described in described locked clip device.The present invention passes through wear ring under the coupling mechanism force and pressure effect of clip, the damping torque producing with front-wheel strut friction to prevent shimmy of front wheels it is ensured that preventing while shimmy of front wheels effect so that the structure of vibration absorber is simple, small volume, lightweight and substantially reduce cost.
Description
Technical field
The present invention relates to one kind subtracts shimmy device, more particularly, to a kind of device preventing front-wheel shimmy of airplane.
Background technology
When taking off or alighting run, front-wheel produces a kind of wheel neutral position of deviateing in lateral and torsion to aircraft sometimes
The high vibration that direction intercouples, this vibration is referred to as shimmy.Front-wheel shimmy of airplane be by pillar, the lateral vibration of front-wheel with
Front-wheel twisting vibration around pillar axes intercouples caused a kind of extremely complex self-excited vibration, maintains this self-excitation
The energy of vibration be aircraft is sliding run during provided by power on tire for the ground effects and moment, when shimmy violent, with
The high vibration of Shi Yinqi fuselage, has a strong impact on the normal operational of driver, or even causes the destruction of body parts or accident
Occur, therefore shimmy of front wheels is a kind of very harmful self-excited vibration it is necessary to be prevented.And the fluid of existing employing subtracts pendulum dress
Put, using fluid, wheel shimmy is prevented by the moment that the damping force that aperture produces produces.But this shimmy damping device structure
Complexity, volume are big, weight is heavy and high cost.
Content of the invention
For solving the shortcomings and deficiencies of the existing shimmy damping device preventing front-wheel shimmy of airplane, technology to be solved by this invention
Problem be provide that a kind of structure is simple, the device preventing front-wheel shimmy of airplane of small volume, lightweight and low cost.
In order to solve the problems, such as prior art, the technical solution used in the present invention is：One kind prevents aircraft nose wheel from putting
The device shaking, it includes being set on aircraft nose wheel pillar and be provided with the wear ring of opening, is set in outside described wear ring
Clip, it is sheathed on described clip opening and by the bolt assembly of wear ring described in described locked clip device.
Prevent the improvement of the device technique scheme of front-wheel shimmy of airplane as the present invention, described bolt assembly is arranged with
Adjust spring, described regulation spring is located between described clip opening side and nut.
Prevent the improvement further of the device technique scheme of front-wheel shimmy of airplane as the present invention, described wear ring is non-gold
Belong to wear ring.It is preferred that described wear ring is PVC wear ring.
With respect to prior art, a kind of advantage of the device preventing front-wheel shimmy of airplane of the present invention is：By wear ring
Under the coupling mechanism force and pressure effect of clip, the damping torque producing with front-wheel strut friction to prevent shimmy of front wheels it is ensured that preventing
The structure only making vibration absorber while shimmy of front wheels effect is simple, small volume, lightweight and substantially reduce cost.
Brief description
Fig. 1 is a kind of structural representation of the device preventing front-wheel shimmy of airplane of the present invention.
In figure, 1 is front wheel support upright；2 is wear ring；
21 is wear ring opening；3 is clip；
31 is opening；4 is bolt assembly；
41 is nut；42 is bolt；
5 is to adjust spring.
Specific embodiment
Prevent the specific embodiment of the device of front-wheel shimmy of airplane in conjunction with the brief description present invention.
Refer to shown in Fig. 1, the present invention prevent the device of front-wheel shimmy of airplane from including being set on aircraft nose wheel pillar 1 and
The wear ring 2 being provided with opening 21, the clip 3 being set in wear ring 2 outside, it is sheathed on clip opening 31 and passes through locked clip device
The bolt assembly 4 of wear ring.
Wherein, described wear ring 2 is nonmetallic wear ring；It is preferred that described wear ring is PVC wear ring.
Described clip is metal clip.By locking and pressure effect, wear ring 2 and the front-wheel of bolt assembly 4 and clip 3
Pillar 1 friction produces frictional damping moment, weakens or offset the lateral of front-wheel and pillar using the frictional damping moment of wear ring
Shaking moment, thus prevent the shimmy of front-wheel.
It is preferred that being arranged with regulation spring 5 on the bolt 42 of bolt assembly 4, described regulation spring 5 is located at clip opening
Hold between 31 sides and nut 41, by selecting the wear ring 2 of different coefficients of friction or the regulation of different-stiffness and compression height
Spring 5 is realized adjusting the frictional damping moment of wear ring, preferably prevents the shimmy of front-wheel.
The present invention passes through wear ring under the coupling mechanism force and pressure effect of clip, the damping force producing with front-wheel strut friction
Square come to prevent shimmy of front wheels it is ensured that prevent from making while shimmy of front wheels effect vibration absorber structure is simple, small volume, weight
Light and substantially reduce cost；And the aircraft nose wheel according to different model and machine, by selecting the wear-resisting of different coefficients of friction
The regulation spring of ring and different-stiffness and compression height is realized adjusting frictional damping moment.
Embodiment described above only have expressed the several embodiments of the present invention, and its description is more concrete and detailed, but simultaneously
Therefore the restriction to the scope of the claims of the present invention can not be interpreted as.It should be pointed out that for those of ordinary skill in the art
For, without departing from the inventive concept of the premise, some deformation can also be made and improve, these broadly fall into the guarantor of the present invention
Shield scope.Therefore, the protection domain of patent of the present invention should be defined by claims.
Claims (3)
1. a kind of device preventing front-wheel shimmy of airplane it is characterised in that：Including being set on aircraft nose wheel pillar and be provided with out
Mouthful wear ring, be set in clip outside described wear ring, be sheathed on described clip opening and pass through described locked clip device
The bolt assembly of described wear ring, is arranged with regulation spring, described regulation spring is located at described clip on described bolt assembly
Between opening side and nut.
2. the device preventing front-wheel shimmy of airplane according to claim 1 it is characterised in that：Described wear ring is nonmetallic
Wear ring.
3. the device preventing front-wheel shimmy of airplane according to claim 2 it is characterised in that：Described wear ring is that PVC is resistance to
Bull ring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310126716.1A CN103171761B (en) | 2013-04-12 | 2013-04-12 | A kind of device preventing front-wheel shimmy of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310126716.1A CN103171761B (en) | 2013-04-12 | 2013-04-12 | A kind of device preventing front-wheel shimmy of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103171761A CN103171761A (en) | 2013-06-26 |
| CN103171761B true CN103171761B (en) | 2017-03-01 |
Family
ID=48632059
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310126716.1A Active CN103171761B (en) | 2013-04-12 | 2013-04-12 | A kind of device preventing front-wheel shimmy of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103171761B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043674A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Method for avoiding shimmy of main undercarriage under high-speed condition |
| CN109611613A (en) * | 2019-01-23 | 2019-04-12 | 辽宁科技大学 | A kind of fluid pressure line test pipeline connecting device of multi-pipeline multiclass support stiffness |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201800917U (en) * | 2010-09-30 | 2011-04-20 | 湖南山河科技股份有限公司 | Anti-shimmy mechanism of landing wheel |
| CN102405358A (en) * | 2009-04-06 | 2012-04-04 | 梅西耶-布加蒂-道提公司 | Landing gear provided with a selective force transmission device |
| CN202624631U (en) * | 2012-06-08 | 2012-12-26 | 中国航空工业集团公司西安飞机设计研究所 | Locking ring swing control device for landing gear |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2161312Y (en) * | 1993-05-04 | 1994-04-13 | 畅君臣 | Infusion bottle interlocking band |
| US7090606B2 (en) * | 2003-07-03 | 2006-08-15 | The Gates Corporation | Adjustable tensioner |
| FR2887517B1 (en) * | 2005-06-28 | 2008-09-12 | Airbus France Sas | STEERING DEVICE WITH REDUCED SIZE FOR AIRCRAFT LANDFILL |
-
2013
- 2013-04-12 CN CN201310126716.1A patent/CN103171761B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102405358A (en) * | 2009-04-06 | 2012-04-04 | 梅西耶-布加蒂-道提公司 | Landing gear provided with a selective force transmission device |
| CN201800917U (en) * | 2010-09-30 | 2011-04-20 | 湖南山河科技股份有限公司 | Anti-shimmy mechanism of landing wheel |
| CN202624631U (en) * | 2012-06-08 | 2012-12-26 | 中国航空工业集团公司西安飞机设计研究所 | Locking ring swing control device for landing gear |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103171761A (en) | 2013-06-26 |
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| TR01 | Transfer of patent right |
Effective date of registration: 20190516 Address after: 313219 Starting Road of General Aviation Industrial Park, Leidian Town, Deqing County, Huzhou City, Zhejiang Province (Mogan Mountain National High-tech Zone) Patentee after: Zhejiang China Airlines Flight Research Institute Co., Ltd. Address before: 519040 Room 218, 2nd floor, Building 3, Xiasha Street, Wanchai, Zhuhai City, Guangdong Province Patentee before: China Aviation Industry General Aircraft Co., Ltd. |
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| TR01 | Transfer of patent right |