CN104210651A - Landing gear connecting structure - Google Patents
Landing gear connecting structure Download PDFInfo
- Publication number
- CN104210651A CN104210651A CN201410424847.2A CN201410424847A CN104210651A CN 104210651 A CN104210651 A CN 104210651A CN 201410424847 A CN201410424847 A CN 201410424847A CN 104210651 A CN104210651 A CN 104210651A
- Authority
- CN
- China
- Prior art keywords
- connecting pin
- hole
- bolt
- nut
- end covers
- 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.)
- Pending
Links
Classifications
-
- 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
- Gears, Cams (AREA)
Abstract
The invention relates to a landing gear connecting structure, which comprises a bolt, end covers, a connecting pin and a nut, wherein a boss is arranged in the middle of one side of the end cover, a through hole is formed in the middle of the boss, a through hole is formed axially in the connecting pin, the connecting pin penetrates through a mounting holes of a fuselage joint and a damper leg, the end covers are arranged on two ends of the connecting pin, the boss structures in the middle of the end covers extend into the through hole of the connecting pin, the axes of the through holes of the end covers and the axis of the through hole of the connecting pin are in one line, the bolt penetrates through the through holes in the end covers and is fixed through the nut. The landing gear connecting structure has the beneficial effect of bearing higher shear load and small axial load. The connecting pin has a hollow cylinder structure, thus being simple in structure, and convenient to machine and manufacture; the end covers are made of aluminum or other equivalent materials, so that the weight of the structure can be effectively lightened; the bolt with small axial diameter bears the axial load, and the weight reduction effect can achieve more than 30% compared with a common bolt connecting structure.
Description
Technical field
The invention belongs to Landing Gear Design technology, relate to the design of a kind of alighting gear connection structure.
Background technology
Alighting gear connection structure is applied to a connection for articulated landing gear damper leg and airframe structure, by damper leg dynamic changes process on airframe structure, and can realize the rotation of damper leg within the scope of certain angle.
Alighting gear connection structure is power transmission critical parts, and it mainly bears shearing load.As shown in Figure 1, the auxiliary connection that current most of alighting gear connection structure is the bolt made of high strength steel or hollow bolt (1), packing ring (2), nut (3) combine with spring cotter (4), the connection structure of this conventional design bears shearing load by bolt (1), for barrel bolt (1), nut (3) size selected is larger, the length of bolt (1) is also longer, therefore, the weight cost paid is larger.
Summary of the invention
Object of the present invention: design a kind of alighting gear connection structure, effectively can transmit shearing load, can alleviate structural weight cost simultaneously.
Technical scheme of the present invention: a kind of alighting gear connection structure, it is characterized in that: comprise bolt (1), end cap (3), connecting pin (4) and nut (5), end cap (3) one middle side part has boss, centre has through hole, connecting pin (4) axially has through hole, connecting pin (4) is through the mounting hole of body joint and damper leg, end cap (3) is installed at connecting pin (4) two ends, the boss structure at end cap (3) middle part stretches into the through hole of connecting pin (4), and the axis of the axis of end cap (3) through hole and connecting pin (4) through hole point-blank, bolt (1) is through the through hole of end cap (3) and connecting pin (4), fixed by nut (5).
Beneficial effect of the present invention: a kind of alighting gear connection structure, can bear larger shearing load, and less axial load.Connecting pin is hollow cylinder structure, and configuration is simple, is convenient to processing and manufacturing; End cap is aluminium or other equivalent material product, can alleviate structural weight by actv.; Adopt the bolt that the diameter of axle is less to transmit axial load, relative to general bolt fastening structure, its weight loss effect can reach more than 30%.
Accompanying drawing explanation
Fig. 1 is conventional Take-off and Landing frame connecting structure isometric views
Fig. 2 is a kind of alighting gear connection structure of the present invention isometric views
Fig. 3 is a kind of alighting gear connection structure of the present invention cutaway view
Fig. 4 is the end cap isometric views in a kind of alighting gear connection structure of the present invention
Detailed description of the invention
Connecting pin (4) is power transmission critical parts, mainly bear shearing load, employing high strength steel is made, determine the dimension of inner and outer diameters of connecting pin (4) according to the size of alighting gear joint load and the aperture of joint knuckle bearing, its length should than the width between body joint end face little 0.5 ~ 2mm; The fastener that bolt (1), packing ring (2) and nut (5) form transmits axial force, play the role of fastening, according to size determination bolt (1) shank diameter of axial force, nut (5) preferentially selects hexagonal fluting self lock nut, duplicate protection is formed with spring cotter (6), for locking, fastener or adopt other to have the fastener constructions of locking measure; End cap (3) is aluminium or other equivalent material product, be assemblied in connecting pin (4) hole, for connecting pin (4) provide spacing, fixation, coming off of connecting pin (4) can be prevented, axial load can be passed simultaneously, end cap (3) is diametrically greater than connecting pin (4) external diameter outward, the two ends being clamped in body joint can be met, inside diametrically be slightly less than connecting pin (4) aperture, fit system between interior edge and connecting pin (4) hole is free-running fit, and end cap (3) center bore should 0.5 ~ 1mm larger than bolt (1) diameter.
Claims (3)
1. an alighting gear connection structure, it is characterized in that: comprise bolt (1), end cap (3), connecting pin (4) and nut (5), end cap (3) one middle side part has boss, centre has through hole, connecting pin (4) axially has through hole, connecting pin (4) is through the mounting hole of body joint and damper leg, end cap (3) is installed at connecting pin (4) two ends, the boss structure at end cap (3) middle part stretches into the through hole of connecting pin (4), and the axis of the axis of end cap (3) through hole and connecting pin (4) through hole point-blank, bolt (1) is through the through hole of end cap (3) and connecting pin (4), fixed by nut (5).
2. alighting gear connection structure according to claim 1, it is characterized in that: described nut (5) is hexagon slotted nut, bolt (1) end radial direction has through hole, spring cotter (6), through nut (5) and bolt (1), plays locking effect.
3. alighting gear connection structure according to claim 1, is characterized in that: described nut (5) is self lock nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410424847.2A CN104210651A (en) | 2014-08-26 | 2014-08-26 | Landing gear connecting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410424847.2A CN104210651A (en) | 2014-08-26 | 2014-08-26 | Landing gear connecting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104210651A true CN104210651A (en) | 2014-12-17 |
Family
ID=52092656
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410424847.2A Pending CN104210651A (en) | 2014-08-26 | 2014-08-26 | Landing gear connecting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104210651A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104942029A (en) * | 2015-06-25 | 2015-09-30 | 江苏永钢集团有限公司 | Cantilever type high-strength slitting guide anti-loosening device |
| CN108528678A (en) * | 2018-06-11 | 2018-09-14 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter buffering bindiny mechanism |
| CN108910021A (en) * | 2018-07-25 | 2018-11-30 | 苏州频聿精密机械有限公司 | A kind of undercarriage mounting connection structure |
| CN112173084A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Retractable main landing gear bearing structure of unmanned high-speed helicopter and design method thereof |
| CN113928542A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Undercarriage bearing structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201354809Y (en) * | 2009-01-08 | 2009-12-02 | 太原市通泽成套设备有限公司 | Rolling mill frame safety coupling |
| CN101708445A (en) * | 2009-11-27 | 2010-05-19 | 河南黄河旋风股份有限公司 | Hollow pin shaft of cubic hinge press |
| CN103032434A (en) * | 2012-11-26 | 2013-04-10 | 中国商用飞机有限责任公司 | Fail-safe safety pin |
| CN203497167U (en) * | 2013-08-30 | 2014-03-26 | 中航飞机起落架有限责任公司 | Link mechanism of undercarriage and cabin door |
-
2014
- 2014-08-26 CN CN201410424847.2A patent/CN104210651A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201354809Y (en) * | 2009-01-08 | 2009-12-02 | 太原市通泽成套设备有限公司 | Rolling mill frame safety coupling |
| CN101708445A (en) * | 2009-11-27 | 2010-05-19 | 河南黄河旋风股份有限公司 | Hollow pin shaft of cubic hinge press |
| CN103032434A (en) * | 2012-11-26 | 2013-04-10 | 中国商用飞机有限责任公司 | Fail-safe safety pin |
| CN203497167U (en) * | 2013-08-30 | 2014-03-26 | 中航飞机起落架有限责任公司 | Link mechanism of undercarriage and cabin door |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104942029A (en) * | 2015-06-25 | 2015-09-30 | 江苏永钢集团有限公司 | Cantilever type high-strength slitting guide anti-loosening device |
| CN108528678A (en) * | 2018-06-11 | 2018-09-14 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter buffering bindiny mechanism |
| CN108910021A (en) * | 2018-07-25 | 2018-11-30 | 苏州频聿精密机械有限公司 | A kind of undercarriage mounting connection structure |
| CN108910021B (en) * | 2018-07-25 | 2021-11-30 | 苏州市东挺河智能科技发展有限公司 | Undercarriage erection joint structure |
| CN112173084A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Retractable main landing gear bearing structure of unmanned high-speed helicopter and design method thereof |
| CN113928542A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Undercarriage bearing structure |
| CN113928542B (en) * | 2021-11-19 | 2023-09-01 | 中国直升机设计研究所 | Landing gear bearing structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20141217 |
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| RJ01 | Rejection of invention patent application after publication |