CN211543882U - Rocker arm of undercarriage - Google Patents
Rocker arm of undercarriage Download PDFInfo
- Publication number
- CN211543882U CN211543882U CN201922395074.0U CN201922395074U CN211543882U CN 211543882 U CN211543882 U CN 211543882U CN 201922395074 U CN201922395074 U CN 201922395074U CN 211543882 U CN211543882 U CN 211543882U
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- CN
- China
- Prior art keywords
- rocker arm
- landing gear
- rocker
- undercarriage
- sleeve
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- 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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- 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
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Abstract
The utility model provides an undercarriage rocking arm is provided with the trompil on the sleeve of rocking arm, regards the gap of the inside lightening hole of undercarriage rocking arm barrel and wheel hub connection department as drainage channel, and the steam that gets into the undercarriage structure passes through drainage channel discharge organism outside to reach the anticorrosive requirement of drainage. The structure form of gap fit is adopted as the drainage channel, the structure design is simple and practical, redundant parts are not added, and the weight reduction requirement of the large aircraft landing gear is met.
Description
Technical Field
The utility model relates to an aircraft design field, concretely relates to undercarriage rocking arm.
Background
Parts of the aircraft landing gear structure are prone to ingress and retention of water vapor, which is a harmful medium that causes corrosion of parts. If the waterproof and drainage design is not good, the corrosion fatigue of parts can be caused, the strength of the structural part is reduced, and even the airplane is seriously accident-caused. The waterproof and drainage design of the landing gear is therefore such that no liquid accumulation occurs as far as possible at any point of the component.
The undercarriage design of current model all adopts waterproof design, increases sealed flap and prevents that steam from getting into inside the organism. The large-scale aircraft landing gear has larger volume of parts, unnecessary weight is increased by adopting the design of the traditional waterproof cover, and therefore, the design of the large-scale landing gear needs to have a water vapor discharge measure, but the landing gear design of the protection measure is not available at present.
SUMMERY OF THE UTILITY MODEL
The utility model provides an undercarriage rocking arm alleviates the great problem of weight of current aircraft steam emission design existence.
The utility model provides an undercarriage rocking arm contains: the rocker arm comprises a rocker arm body 1 and a sleeve 2 arranged at one end of the rocker arm body 1; an airplane wheel shaft 3 is arranged in the sleeve 2;
the sleeve 2 is provided with an opening; the opening is located on the axis of the rocker arm body 1.
Optionally, a gap between the inner wall of the sleeve 2 and the wheel axle 3 is not less than 5 mm.
Optionally, the size of the through hole is consistent with that of a through hole at a position where the sleeve 2 and the rocker arm body 1 are in contact with each other.
Optionally, the diameter of an inner hole of one end of the rocker arm body 1 away from the wheel axle 3 is larger than the diameter of an inner hole of one end of the rocker arm body 1 close to the wheel axle 3.
Optionally, a lug 4 for connecting a buffer is arranged on the rocker arm body 1;
the inner hole of one section of the rocker arm body 1 connected with the lug 4 is conical.
Optionally, the diameter of an inner hole of a section of the rocker arm body 1, to which the lug 4 is not connected, is kept unchanged.
The utility model provides an undercarriage rocking arm is provided with the trompil on the sleeve of rocking arm, regards the gap of the inside lightening hole of undercarriage rocking arm barrel and wheel hub connection department as drainage channel, and the steam that gets into the undercarriage structure passes through drainage channel discharge organism outside to reach the anticorrosive requirement of drainage. The structure form of gap fit is adopted as the drainage channel, the structure design is simple and practical, redundant parts are not added, and the weight reduction requirement of the large aircraft landing gear is met.
Drawings
Fig. 1 is a first structural schematic diagram of a landing gear rocker arm down state provided by the utility model;
fig. 2 is a second schematic structural view of the landing gear rocker arm in a down state provided by the present invention;
fig. 3 is a third schematic structural view of the landing gear rocker arm in a down state provided by the present invention;
fig. 4 is a schematic structural diagram of a retraction state of the landing gear rocker arm provided by the present invention.
Description of reference numerals:
1-rocker arm body; 2, a sleeve; 3-wheel axle; 4-lugs connecting the buffers;
5-water vapor passage; 6-landing gear wheels; 7-connecting lug of rocker arm and pillar.
Detailed Description
The landing gear rocker arm provided by the invention is explained below with reference to the attached drawings.
Fig. 1 is the utility model provides a landing gear rocking arm puts down the structural schematic diagram of state one, fig. 2 is the utility model provides a landing gear rocking arm puts down the structural schematic diagram of state two, fig. 3 is the utility model provides a landing gear rocking arm puts down the structural schematic diagram of state three, as shown in fig. 1-3, the landing gear rocking arm contains: the rocker arm comprises a rocker arm body 1 and a sleeve 2 arranged at one end of the rocker arm body 1; an airplane wheel shaft 3 is arranged in the sleeve 2;
the wheel shaft 3 is connected with a landing gear wheel 6;
the sleeve 2 is provided with an opening which is positioned on the axis of the rocker arm body 1 and is used as a drainage channel. For example, the landing gear rocker and landing gear strut attachment tabs 7 may be a water vapor inlet and the sleeve openings may be water vapor outlets. Optionally, the size of the through hole is consistent with that of a through hole at the position where the sleeve 2 and the rocker arm body 1 are in contact with each other.
A conical lightening hole (also called a rocker lightening hole) is designed in the rocker arm of the landing gear, and a gap is designed at the matching position of the rocker lightening hole and the wheel axle, and is optional, and the gap is not smaller than 5 mm.
The diameter of an inner hole of one end (the upper part of the rocker arm lightening hole) of the rocker arm body 1 far away from the wheel axle 3 is larger than that of one end (the lower part of the rocker arm lightening hole) of the rocker arm body 1 close to the wheel axle 3.
Optionally, a lug 4 for connecting a buffer is arranged on the rocker arm body 1;
the inner hole of one section of the rocker arm body 1 connected with the lug 4 is conical.
Optionally, the diameter of an inner hole of a section of the rocker arm body 1, to which the lug 4 is not connected, is kept unchanged.
The conical lightening hole is formed in the rocker arm, so that the weight of the rocker arm can be further lightened.
Illustratively, when the aircraft lands, the water vapor on the runway enters the inner part of the rocker arm lightening hole of the undercarriage through the rocker arm lightening hole opening and then is discharged out of the aircraft body through the water vapor passage 5.
Fig. 4 is the structural schematic diagram of the state is packed up to undercarriage rocking arm, as shown in fig. 4, after the aircraft takes off, the undercarriage is packed up, rocking arm lightening hole upper portion rotates to opening state down, gets into the inside steam of undercarriage lightening hole then by direct discharge on rocking arm lightening hole upper portion, has avoided the undercarriage to pack up the back, the gathering of steam.
Claims (6)
1. A landing gear rocker arm, comprising: the rocker arm comprises a rocker arm body (1) and a sleeve (2) arranged at one end of the rocker arm body (1); an airplane wheel shaft (3) is arranged in the sleeve (2);
the sleeve (2) is provided with an opening; the opening is located on the axis of the rocker arm body (1).
2. Landing gear rocker according to claim 1, wherein the gap between the inner wall of the sleeve (2) and the wheel axle (3) is not less than 5 mm.
3. Landing gear rocker according to claim 1, wherein the aperture corresponds to the size of the through hole where the sleeve (2) and the rocker body (1) are in common.
4. Landing gear rocker arm according to claim 1, characterized in that the inner bore diameter of the rocker arm body (1) at the end remote from the wheel axle (3) is larger than the inner bore diameter of the rocker arm body (1) at the end close to the wheel axle (3).
5. Landing gear rocker according to claim 4, wherein the rocker body (1) is provided with a tab (4) for connection of a buffer;
the inner hole of one section of the rocker arm body (1) connected with the lug (4) is conical.
6. Landing gear rocker according to claim 5, wherein the diameter of the inner bore of the section of the rocker body (1) to which the tab (4) is not connected remains constant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922395074.0U CN211543882U (en) | 2019-12-26 | 2019-12-26 | Rocker arm of undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922395074.0U CN211543882U (en) | 2019-12-26 | 2019-12-26 | Rocker arm of undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211543882U true CN211543882U (en) | 2020-09-22 |
Family
ID=72510258
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922395074.0U Active CN211543882U (en) | 2019-12-26 | 2019-12-26 | Rocker arm of undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211543882U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114261533A (en) * | 2021-12-31 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear pneumatic load simulation device |
-
2019
- 2019-12-26 CN CN201922395074.0U patent/CN211543882U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114261533A (en) * | 2021-12-31 | 2022-04-01 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft landing gear pneumatic load simulation device |
| CN114261533B (en) * | 2021-12-31 | 2024-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic load simulator of aircraft landing gear |
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| GR01 | Patent grant |