CN106043674A - Method for avoiding shimmy of main undercarriage under high-speed condition - Google Patents
Method for avoiding shimmy of main undercarriage under high-speed condition Download PDFInfo
- Publication number
- CN106043674A CN106043674A CN201610374214.4A CN201610374214A CN106043674A CN 106043674 A CN106043674 A CN 106043674A CN 201610374214 A CN201610374214 A CN 201610374214A CN 106043674 A CN106043674 A CN 106043674A
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- CN
- China
- Prior art keywords
- shimmy
- landing gear
- main landing
- counterweight
- wheel shaft
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gears, Cams (AREA)
Abstract
The invention relates to a method for avoiding the shimmy of a main undercarriage under a high-speed condition. A balance weight is arranged at the center line perpendicular to the axis of a main undercarriage axle and used for eliminating or reducing the shimmy of the main undercarriage under the high-speed condition. The method for avoiding the shimmy of the main undercarriage under the high-speed condition has the beneficial effects of being simple, easy to implement, wide in application range, low in cost and the like.
Description
Technical field
The invention belongs to aviation undercarriage technical field, particularly relate to a kind of avoid under main landing gear high-speed case shimmy
Method.
Background technology
The shimmy deviation wheel neutral position that wheel produces when referring to take off or alighting run is in lateral and torsion side
To the high vibration phenomenon intercoupled, deploy and can have a strong impact on pilot control aircraft, cause structure fatigue damage to evoke knot
Structure resonates, and causes structural deterioration, cause the generation of disaster time serious.The shimmy phenomenon of aircraft typically occurs in nose-gear, but
Main landing gear also has the situation that generation is shimmy, and current solution is usually to install between the most anti-torque arm of main landing gear and subtracts pendulum
Device, but shimmy-damper is installed there is price, cost height, safeguard the shortcomings such as inconvenience.
Summary of the invention
It is an object of the invention to provide and a kind of avoid method shimmy under main landing gear high-speed case, solve the problems referred to above.
For reaching above-mentioned purpose, the technical solution used in the present invention is: one is avoided under main landing gear high-speed case shimmy
Method, at the centrage being perpendicular to main landing gear wheel shaft axis, counterweight is set, described counterweight is for eliminating or reducing main rising and falling
Shimmy under frame high-speed case.
Further, described counterweight contacts fixing with described wheel shaft, or described counterweight is connected to described wheel by support member
Axle and be placed in the front of described wheel shaft, described front is vector direction.
Further, if described counterweight is connected to described wheel shaft by support member, the most described support member is parallel to horizontal plane,
Described wheel shaft is fixed in one end of described support member, and the support member other end is fixed with described counterweight.
Further, adjust the runout effect under main landing gear high-speed case by the quality adjusting described counterweight, or
The runout effect under main landing gear high-speed case is adjusted, described support member a length of by the length adjusting described support member
The barycenter of the described counterweight distance away from described axle axis.
Further, the quality of described counterweight is the most greatly for the shimmy effect eliminating or reducing under main landing gear high-speed case
The best, the barycenter of the described counterweight distance away from described axle axis is the longest for eliminating or reducing under main landing gear high-speed case
Shimmy effect is the best.
It is simple that the present invention a kind of avoids method shimmy under main landing gear high-speed case to have method, the scope of application
Extensively, low cost and other advantages.
Accompanying drawing explanation
Accompanying drawing herein is merged in description and constitutes the part of this specification, it is shown that meet the enforcement of the present invention
Example, and for explaining the principle of the present invention together with description.
Fig. 1 is counterweight scheme of installation at undercarriage crop rotation；
Fig. 2 is counterweight 5kg shimmy range of instability schematic diagram；
Fig. 3 is counterweight 25kg shimmy range of instability schematic diagram；
Fig. 4 is counterweight 50kg shimmy range of instability schematic diagram.
Wherein, 1-wheel, 2-wheel shaft, 3-support member, 4-counterweight.
Detailed description of the invention
Clearer for the purpose making the present invention implement, technical scheme and advantage, below in conjunction with in the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, the most identical or class
As label represent same or similar element or there is the element of same or like function.Described embodiment is the present invention
A part of embodiment rather than whole embodiments.The embodiment described below with reference to accompanying drawing is exemplary type, it is intended to use
In explaining the present invention, and it is not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under not making creation type work premise, broadly falls into the scope of protection of the invention.Under
Face combines accompanying drawing and is described in detail embodiments of the invention.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ", "front", "rear",
The orientation of the instruction such as "left", "right", " vertically ", " level ", " top ", " end ", " interior ", " outward " or position relationship are for based on accompanying drawing institute
The orientation shown or position relationship, be for only for ease of and describe the present invention and simplify description rather than instruction or the dress of hint indication
Put or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that protect the present invention
The restriction of scope.
With an instantiation or result of the test, the present invention is described in further details below.As shown in Figure 1, it is known that certain type
Aircraft main landing gear is two-wheel telescopic landing gear, has led the shimmy phenomenon of generation, existing difference in the case of not installing shimmy-damper
Before and after the counterweight (5kg, 25kg, 50kg) of different quality is installed on wheel shaft at a certain distance (-0.6m～0.6m).
Shown in implementation result as Fig. 2 to Fig. 4, along with the increase of counterweight 4 mass, shimmy unstable region (stain institute in figure
Show) gradually decreasing；If singly seeing shown in Fig. 4, in counterweight 4 one timing, counterweight 4 installation site is more remote from center pendulum and shakes phenomenon more
Few, and counterweight 4 be installed on wheel shaft 2 before (distance be negative) be installed on wheel shaft 2 than counterweight 4 after (apart from being just) effect is more
Significantly.
In sum, before counterweight 4 is installed on wheel shaft 2 (distance is negative), along with the increase of counterweight 4 mass, shimmy shakiness
Determine district to be gradually reduced, the most at high speeds；After counterweight 4 is installed on wheel shaft 2 (distance is for just), along with counterweight 4 mass
Increase, shimmy range of instability is gradually reduced, the most at high speeds.
The a kind of of the present invention avoids method shimmy under main landing gear high-speed case simple and effective, easy to implement, only need by
The counterweight of constant weight is installed on wheel shaft front at a certain distance；The method low cost, counterweight materials and processing cost are low；This side
Method highly versatile, army's civil aircraft is the most available.
The above, the only optimum detailed description of the invention of the present invention, but protection scope of the present invention is not limited thereto,
Any those familiar with the art in the technical scope that the invention discloses, the change that can readily occur in or replacement,
All should contain within protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of described claim
Enclose and be as the criterion.
Claims (5)
1. avoid method shimmy under main landing gear high-speed case for one kind, it is characterised in that be perpendicular to main landing gear wheel shaft (2)
The centrage of axis arranges counterweight (4), described counterweight (4) for eliminate or reduce under main landing gear high-speed case shimmy.
The most according to claim 1 avoid method shimmy under main landing gear high-speed case, it is characterised in that described counterweight
(4) contacting fixing with described wheel shaft (2), or described counterweight (4) is connected to described wheel shaft (2) by support member (3) and is placed in institute
Stating the front of wheel shaft (2), described front is vector direction.
The most according to claim 2 avoid method shimmy under main landing gear high-speed case, it is characterised in that join described in if
Weight (4) is connected to described wheel shaft (2) by support member (3), and the most described support member (3) is parallel to level, described support member (3)
Described wheel shaft (2) is fixed in one end, and support member (3) other end is fixed with described counterweight (4).
The most according to claim 3 avoid method shimmy under main landing gear high-speed case, it is characterised in that by adjusting
The quality of described counterweight (4) adjusts the runout effect under main landing gear high-speed case, or by adjusting described support member (3)
Length adjusts the runout effect under main landing gear high-speed case, the barycenter of a length of described counterweight (4) of described support member (3)
Distance away from described wheel shaft (2) axis.
The most according to claim 4 avoid method shimmy under main landing gear high-speed case, it is characterised in that described counterweight
(4) the shimmy effect that quality is used for the most greatly eliminating or reducing under main landing gear high-speed case is the best, the barycenter of described counterweight (4)
The longest shimmy effect for eliminating or reduce under main landing gear high-speed case of distance away from described wheel shaft (2) axis is the best.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610374214.4A CN106043674A (en) | 2016-05-31 | 2016-05-31 | Method for avoiding shimmy of main undercarriage under high-speed condition |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610374214.4A CN106043674A (en) | 2016-05-31 | 2016-05-31 | Method for avoiding shimmy of main undercarriage under high-speed condition |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106043674A true CN106043674A (en) | 2016-10-26 |
Family
ID=57173090
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610374214.4A Pending CN106043674A (en) | 2016-05-31 | 2016-05-31 | Method for avoiding shimmy of main undercarriage under high-speed condition |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106043674A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2661916A (en) * | 1950-02-13 | 1953-12-08 | Electro Hydraulies Ltd | Airplane landing gear |
| US2892450A (en) * | 1955-02-23 | 1959-06-30 | Cleveland Pneumatic Ind Inc | Control valve |
| US2943818A (en) * | 1956-03-15 | 1960-07-05 | Cleveland Pneumatic Ind Inc | Steering mechanism |
| 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 |
| CN102602534A (en) * | 2012-04-05 | 2012-07-25 | 中航飞机起落架有限责任公司 | Shimmy damping device for landing gear |
| CN202574614U (en) * | 2012-04-30 | 2012-12-05 | 杭州芬麦特机械有限公司 | Main support device for aircraft landing gear |
| CN103038538A (en) * | 2010-07-29 | 2013-04-10 | 梅西耶-道提股份有限公司 | Hydraulic shimmy damper for aircraft landing gear |
| CN103171761A (en) * | 2013-04-12 | 2013-06-26 | 中航通飞研究院有限公司 | Device for preventing front-wheel shimmy of airplane |
| CN103523217A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Nose-wheel steering system of aircraft |
-
2016
- 2016-05-31 CN CN201610374214.4A patent/CN106043674A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2661916A (en) * | 1950-02-13 | 1953-12-08 | Electro Hydraulies Ltd | Airplane landing gear |
| US2892450A (en) * | 1955-02-23 | 1959-06-30 | Cleveland Pneumatic Ind Inc | Control valve |
| US2943818A (en) * | 1956-03-15 | 1960-07-05 | Cleveland Pneumatic Ind Inc | Steering mechanism |
| CN103038538A (en) * | 2010-07-29 | 2013-04-10 | 梅西耶-道提股份有限公司 | Hydraulic shimmy damper for aircraft landing gear |
| 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 |
| CN102602534A (en) * | 2012-04-05 | 2012-07-25 | 中航飞机起落架有限责任公司 | Shimmy damping device for landing gear |
| CN202574614U (en) * | 2012-04-30 | 2012-12-05 | 杭州芬麦特机械有限公司 | Main support device for aircraft landing gear |
| CN103523217A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Nose-wheel steering system of aircraft |
| CN103171761A (en) * | 2013-04-12 | 2013-06-26 | 中航通飞研究院有限公司 | Device for preventing front-wheel shimmy of airplane |
Non-Patent Citations (1)
| Title |
|---|
| 王轩: ""飞机前轮摆振稳定性分析方法研究"", 《中国优秀硕士学位论文数据库》 * |
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| C06 | Publication | ||
| PB01 | Publication | ||
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Application publication date: 20161026 |