CN202624629U - Rocker type landing gear - Google Patents
Rocker type landing gear Download PDFInfo
- Publication number
- CN202624629U CN202624629U CN 201220186561 CN201220186561U CN202624629U CN 202624629 U CN202624629 U CN 202624629U CN 201220186561 CN201220186561 CN 201220186561 CN 201220186561 U CN201220186561 U CN 201220186561U CN 202624629 U CN202624629 U CN 202624629U
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- CN
- China
- Prior art keywords
- landing gear
- rocking arm
- rocker
- energy disperser
- wheel
- 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 - Lifetime
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Abstract
The utility model belongs to a design technology of a landing gear and relates to a rocker type landing gear. The landing gear comprises a rocker (1), a buffer (2) and a wheel (3), wherein one ends of the rocker (1) and the buffer (2) are approximately parallel to hinge joints (6 and 7) of an airframe respectively; the other end of the buffer (2) is hinged with the rocker (1); a hinge joint (4) is positioned below a connection line (5) of a rotation center of the rocker (1) and the center of the wheel. By the landing gear, application of rocker type landing gear is expanded; the landing gear can be applied to certain special airframes; and the product performance is improved.
Description
Technical field
The utility model belongs to the alighting gear designing technique, relates to a kind of rocker-arm configuration alighting gear.
Background technology
The rocker-arm configuration is the wheel undercarriage configuration that a kind of quilt extensively adopts.Be characterized in that alighting gear has the rocking arm of a rotation, when landing, rotate the compression buffer energy-absorbing through rocking arm.Its advantage is that energy disperser is that two power bar structures only receive axial force, and good airproof performance can bear bigger load, can make full use of stroke that structure space increases alighting gear to absorb more energy through transitive relation in addition.Based on above-mentioned advantage, nearly all helicopter landing gear with anti-crash designing requirement has all adopted the rocker-arm configuration.
As shown in Figure 1, the full extended length of energy disperser is S1, and full compression length is S2.Draft gear travel is S1-S2, and the full extended length of energy disperser is more than 3 times of stroke usually, i.e. S1＞3 (S1-S2).Be subject to some special housing construction; Two point of connection of alighting gear and fuselage are in level or level of approximation is arranged; As can beappreciated from fig. 1; Obviously can't realize the layout of rocker-arm configuration alighting gear by the method for designing of present routine, need then adopt the alighting gear of other configuration, cause properties of product to descend or bring high weight cost.
Summary of the invention
The technical matters that the utility model will solve: propose a kind of alighting gear and two point of connection of fuselage of being applicable to and be in the rocker-arm configuration alighting gear of level or level of approximation layout, to satisfy the needs of some special housing construction.
The technical scheme of the utility model: a kind of articulated landing gear; Comprise rocking arm 1, energy disperser 2, wheel 3; rocking arm 1 and energy disperser 2 one ends are arranged with two fuselage hinge-points, 6,7 level of approximation respectively; said energy disperser 2 other ends and rocking arm 1 are hinged, and hinge-point 4 is positioned at the below of the line 5 at rocking arm 1 center of turn and wheel center.
Said rocking arm 1 is the framed structure of hollow, and energy disperser 2 passes rocking arm 1 hollow space, and is hinged through pivot pin 8 and rocking arm 1.
Said energy disperser 2 is articulated in rocking arm 1 one sides.
The beneficial effect of the utility model: expanded the application of rocker-arm configuration alighting gear, applicable to some special housing construction to improve performance of products.
Description of drawings
Fig. 1 is conventional articulated landing gear scheme drawing.
Fig. 2 is the utility model plan sketch.
Fig. 3 is the structural representation of the utility model one preferred embodiments.
Fig. 4 is another preferred embodiments structural representation of the utility model.
Wherein, 1-rocking arm, 2-energy disperser and 3-wheel, 4-hinge-point, the line at 5-wheel center, 6,7-fuselage hinge-point, 8-pivot pin.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is described in further detail, see also Fig. 2 and Fig. 4.
As shown in Figure 2; A kind of articulated landing gear; Comprise rocking arm 1, energy disperser 2, wheel 3; rocking arm 1 and energy disperser 2 one ends arrange that with two fuselage hinge-points, 6,7 level of approximation said energy disperser 2 other ends and rocking arm 1 are hinged respectively, and hinge-point 4 is positioned at the below of the line 5 at rocking arm 1 center of turn and wheel center.
As shown in Figure 3, rocking arm 1 adopts the framed structure of hollow, and energy disperser 2 passes hollow space, and is hinged through pivot pin 8 and rocking arm.
As shown in Figure 4, energy disperser 2 is articulated in a side of rocking arm 1.
The energy disperser 2 full elongation state length of the utility model are S1, and full compression state length is S2.
The principle of work of the utility model is: rotate around fuselage hinge-point 6 at landing load effect lower shake-changing arm 1 during landing, compression buffer 2 absorbs energy.
Claims (3)
1. articulated landing gear; Comprise rocking arm [1], energy disperser [2], wheel [3]; rocking arm [1] and energy disperser [2] one ends are arranged with two fuselage hinge-points [6,7] level of approximation respectively; it is characterized in that said energy disperser [2] other end and rocking arm [1] are hinged, hinge-point [4] is positioned at the below of the line [5] at rocking arm [1] center of turn and wheel center.
2. a kind of articulated landing gear according to claim 1 is characterized in that, said rocking arm [1] is the framed structure of hollow, and energy disperser [2] passes rocking arm [1] hollow space, and is hinged through pivot pin [8] and rocking arm [1].
3. a kind of articulated landing gear according to claim 1 is characterized in that, said energy disperser [2] is articulated in rocking arm [1] one side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220186561 CN202624629U (en) | 2012-04-27 | 2012-04-27 | Rocker type landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220186561 CN202624629U (en) | 2012-04-27 | 2012-04-27 | Rocker type landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202624629U true CN202624629U (en) | 2012-12-26 |
Family
ID=47377853
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220186561 Expired - Lifetime CN202624629U (en) | 2012-04-27 | 2012-04-27 | Rocker type landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202624629U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104210653A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Rocker arm landing gear |
| CN106585962A (en) * | 2016-11-30 | 2017-04-26 | 中国直升机设计研究所 | External automatic reset device of landing gear |
| CN106965922A (en) * | 2016-01-13 | 2017-07-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of arm-type undercarriage of Novel remote |
| CN110683062A (en) * | 2019-09-29 | 2020-01-14 | 中国直升机设计研究所 | Helicopter tail protection device |
-
2012
- 2012-04-27 CN CN 201220186561 patent/CN202624629U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104210653A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Rocker arm landing gear |
| CN106965922A (en) * | 2016-01-13 | 2017-07-21 | 哈尔滨飞机工业集团有限责任公司 | A kind of arm-type undercarriage of Novel remote |
| CN106965922B (en) * | 2016-01-13 | 2020-06-09 | 哈尔滨飞机工业集团有限责任公司 | Novel rocker arm type undercarriage |
| CN106585962A (en) * | 2016-11-30 | 2017-04-26 | 中国直升机设计研究所 | External automatic reset device of landing gear |
| CN110683062A (en) * | 2019-09-29 | 2020-01-14 | 中国直升机设计研究所 | Helicopter tail protection device |
| CN110683062B (en) * | 2019-09-29 | 2023-04-18 | 中国直升机设计研究所 | Helicopter tail protection device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121226 |