CN108082454B - Undercarriage rocker arm joint mounting structure and method based on self-lubricating bushing - Google Patents
Undercarriage rocker arm joint mounting structure and method based on self-lubricating bushing Download PDFInfo
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- CN108082454B CN108082454B CN201711256541.0A CN201711256541A CN108082454B CN 108082454 B CN108082454 B CN 108082454B CN 201711256541 A CN201711256541 A CN 201711256541A CN 108082454 B CN108082454 B CN 108082454B
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- bushing
- limiting
- self
- mounting hole
- lubricating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P11/00—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for
- B23P11/02—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for by first expanding and then shrinking or vice versa, e.g. by using pressure fluids; by making force fits
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P11/00—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for
- B23P11/02—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for by first expanding and then shrinking or vice versa, e.g. by using pressure fluids; by making force fits
- B23P11/025—Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for by first expanding and then shrinking or vice versa, e.g. by using pressure fluids; by making force fits by using heat or cold
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/02—Parts of sliding-contact bearings
- F16C33/04—Brasses; Bushes; Linings
- F16C33/06—Sliding surface mainly made of metal
- F16C33/10—Construction relative to lubrication
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Valve-Gear Or Valve Arrangements (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention relates to a self-lubricating bushing-based undercarriage rocker arm joint mounting structure and a self-lubricating bushing-based undercarriage rocker arm joint mounting method, which belong to the technical field of helicopter mounting structures. The assembly method based on self-lubrication can realize lubrication of the inner hole and the side wall of the inner bushing which is finally required to be connected with the rocker arm, can meet the high-precision assembly requirement (high coaxiality requirement) of the rocker arm of the landing gear, and can meet the requirement of maintenance-free use in an outfield during the service life of the bushing.
Description
Technical Field
The invention belongs to the technical field of helicopter installation design, and particularly relates to an undercarriage rocker arm joint installation structure and method based on a self-lubricating bushing.
Background
Now according to the general arrangement of the aircraft as shown in fig. 1, the landing gear rocker joint 10 is arranged on a certain main bearing frame 30 to transfer the load of the landing gear 20. The rocker joint 10 adopts a double-lug design which ensures strict form and position tolerance requirements (coaxiality requirements) between lug holes so as to ensure strict assembly precision with the landing gear rocker arm, meanwhile, because the joint of the rocker joint 10 is a high-stress area and has relative motion, wear and fatigue defects are easy to occur, the surface roughness and other wear-resistant lubricating designs of the inner holes and the side surfaces of the left lug 11 and the right lug 12 are ensured, and a wear-resistant lubricating area is required to be shown in figure 2 (a thick line area in the figure).
The currently adopted bushing assembly technology is shown in fig. 3 and 4, four bushings are respectively arranged on two lugs by adopting a temperature difference method, a complementary processing method is adopted after assembly, coaxiality between the four bushings is ensured through boring, an oil filling hole 13 is formed in a rocker arm joint 10, a gap 17 is reserved between two bushings (a left bushing 14 and a right bushing 16) in each lug to serve as an oil filling groove, oil is filled into the two bushings through the oil filling hole 13, and oil storage grooves 16 are formed in the two bushings and store oil, so that long-time lubrication is ensured.
However, in the current assembly method, oil injection is easily insufficient, and lubrication of all areas of the inner wall of the bushing cannot be realized; meanwhile, the side wall of the end face of the bushing cannot be lubricated; meanwhile, oil is often required to be injected regularly, so that the maintenance is inconvenient; the rocker arm of the landing gear is a high stress area, and fatigue cracks are easily generated when the oil injection hole is formed.
Disclosure of Invention
The invention aims to meet the requirements of overall arrangement, installation precision of a rocker joint and wear resistance and lubrication, a self-lubricating bushing with a lubricating liner is selected, a high-precision rocker joint assembling model based on the self-lubricating bushing is designed, the installation of the bushing is realized by adopting a new assembling method, and the maintenance-free requirement of the bushing is realized.
In order to achieve the purpose, the invention adopts the technical scheme that: a landing gear rocker joint mounting structure based on self-lubricating bushings for making the axes of two mounting holes of a rocker joint collinear, comprising:
the outer bushing is provided with a limiting outer end for limiting the outer bushing to move along the axis of the mounting hole and an outer bushing body perpendicular to the limiting outer end, the outer bushing body is mounted in the mounting hole and in interference fit with the mounting hole, and the limiting outer end is attached to the end face of the mounting hole;
the inner bushing is provided with a limiting inner end for limiting the inner bushing to move along the axis of the mounting hole and an inner bushing body perpendicular to the limiting inner end, the inner bushing body is mounted in the outer bushing and is in interference fit with the outer bushing, and the limiting inner end is positioned on one side of the mounting hole far away from the limiting outer end and is attached to the mounting hole; and
and the self-lubricating liner is arranged on the outer surfaces of the limiting outer end and the limiting inner end, which are far away from the mounting joint, and the inner hole surface of the inner bushing body.
Furthermore, the materials of the outer bushing and the inner bushing are selected from materials with linear expansion coefficients and hardness larger than those of the rocker joint.
Further, the material is stainless steel material.
The invention also provides a method for installing the landing gear rocker arm joint based on the self-lubricating bushing, which comprises the following steps:
the method comprises the following steps: the rocker joint is machined and subjected to actual effect treatment, the rocker joint and the outer bushing are assembled by adopting a temperature difference method and are in interference fit, and then the inner hole of the outer bushing is subjected to actual effect treatment to be subjected to complementary processing so that the coaxial precision between the holes of the outer bushing meets the tolerance requirement;
step two: the inner bushing is assembled in an inner hole of the outer bushing at normal temperature by adopting the outer bushing and the rocker joint and by cold shrinkage of the inner bushing, so that the interference fit between the inner bushing and the outer bushing and the installation coaxiality between inner holes of the inner bushing in the two mounting holes are ensured to be within a tolerance range.
The undercarriage rocker arm joint mounting structure and method based on the self-lubricating bushing realize the assembly of the undercarriage rocker arm joint and the self-lubricating bushing, ensure the requirements on assembly precision, lubrication and maintenance-free property, and simultaneously realize the efficient diffusion and transfer of the rocker arm load.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.
Figure 1 is a schematic representation of a prior art landing gear rocker joint arrangement.
FIG. 2 is a schematic view of a prior art bushing at a location where lubrication is required.
FIG. 3 is a schematic illustration of prior art rocker joint oiling.
Fig. 4 is a schematic view of a prior art bushing assembly.
Fig. 5A and 5B are schematic structural views of an outer liner and an inner liner of the present invention, respectively.
Fig. 6 is an installation structure view of the outer liner and the inner liner of the present invention.
Fig. 7 is a view showing an installation structure of the rocker joint and the inner and outer bushes according to the present invention.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
As shown in fig. 5A, 5B and 6, a self-lubricating bushing is adopted in the invention, the self-lubricating bushing is provided with a self-lubricating liner, the self-lubricating liner is divided into an outer bushing 100 and an inner bushing 200, the outer bushing 100 is provided with a limiting outer end 101 for limiting the movement of the outer bushing 200 along the axis of the mounting hole and an outer bushing body 102 perpendicular to the limiting outer end, the outer bushing body 102 is mounted in the mounting hole and is in interference fit with the mounting hole, the limiting outer end 101 is attached to the end surface of the mounting hole, the inner bushing 200 is provided with a limiting inner end 201 for limiting the movement of the inner bushing 200 along the axis of the mounting hole and an inner bushing body 202 perpendicular to the limiting inner end, the inner bushing body 202 is mounted in the outer bushing 200 and is in interference fit with the outer bushing 200, and the limiting inner end 201 is located on one side of the mounting hole far from the limiting outer end 101 and is attached to the mounting hole.
The self-lubricating outer liner 100 has a lubricating pad at the outer end 101, while the self-lubricating inner liner 200 has a lubricating pad at both the inner end 201 and the inner liner body 202.
Because the liner of the self-lubricating bush can not be subjected to complementary processing, and the final installation precision is difficult to ensure by adopting the prior assembly technology, I, the invention realizes the assembly of the rocker arm joint 10 of the undercarriage and the self-lubricating bush by adopting a specific structural form and a process method, ensures the requirements of assembly precision, lubrication and maintenance-free property, and simultaneously realizes the efficient diffusion and transmission of the load of the rocker arm.
The installation structure of the rocker joint 10 and the self-lubricating bushing of the invention is shown in fig. 7, and is installed in a manner of interference fit of an inner bushing and an outer bushing, the outer bushing 100 is in interference fit with the rocker joint 10, the outer bushing 100 is in interference fit with the inner bushing 200 to lubricate an inner hole and a side wall, the rocker joint 10 is made of superhard aluminum alloy material, and the inner bushing and the outer bushing are made of stainless steel material with large linear expansion coefficient, high hardness and wear resistance.
In order to ensure the installation precision of the rocker arm, the coaxiality of the bush in the double lug hole of the rocker arm joint 10 after the self-lubricating bush is assembled needs to be ensured, and the installation interference of the rocker arm joint 10 and the bush needs to be ensured, so the bush is installed by adopting the installation method. Firstly, the rocker arm joint 10 is machined and treated effectively, the rocker arm joint 10 and the outer bushing 100 are assembled by adopting a temperature difference method, large interference is guaranteed, then the inner hole of the outer bushing 100 is subjected to supplementary machining through treatment, high coaxial precision between the inner holes of the outer bushing 100 is guaranteed, then the inner bushing 200 is assembled by adopting a method of shrinking the inner bushing 200 and cooling the outer bushing 100 and the rocker arm joint 10 at normal temperature, the outer bushing 200 and the rocker arm joint 10 are prevented from being heated and deformed, large interference between the inner bushing 200 and the outer bushing 100 and installation coaxiality between the inner holes of the inner bushing 200 are guaranteed, and the installation precision of the helicopter rocker arm can be met through the assembling method.
The assembly method based on self-lubrication can realize lubrication of the inner hole and the side wall of the inner bushing which is finally required to be connected with the rocker arm, can meet the high-precision assembly requirement (high coaxiality requirement) of the rocker arm of the landing gear, and can meet the requirement of maintenance-free use in an outfield during the service life of the bushing.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (2)
1. A landing gear rocker joint mounting structure based on self-lubricating bushings for enabling the axes of two mounting holes of a rocker joint to be collinear, comprising:
the outer bushing is provided with a limiting outer end for limiting the outer bushing to move along the axis of the mounting hole and an outer bushing body perpendicular to the limiting outer end, the outer bushing body is mounted in the mounting hole and in interference fit with the mounting hole, and the limiting outer end is attached to the end face of the mounting hole;
the inner bushing is provided with a limiting inner end for limiting the inner bushing to move along the axis of the mounting hole and an inner bushing body perpendicular to the limiting inner end, the inner bushing body is mounted in the outer bushing and is in interference fit with the outer bushing, and the limiting inner end is positioned on one side of the mounting hole far away from the limiting outer end and is attached to the mounting hole; and
the self-lubricating liner is arranged on the outer surface of the limiting outer end and the limiting inner end, which are far away from the mounting joint, and the inner hole surface of the inner bushing body;
the materials of the outer bushing and the inner bushing are selected from materials with linear expansion coefficients and hardness larger than those of the rocker joint;
the installation process of the landing gear rocker joint comprises the following steps:
the method comprises the following steps: the rocker joint is machined and subjected to actual effect treatment, the rocker joint and the outer bushing are assembled by adopting a temperature difference method and are in interference fit, and then the inner hole of the outer bushing is subjected to actual effect treatment to be subjected to complementary processing so that the coaxial precision between the holes of the outer bushing meets the tolerance requirement;
step two: the inner bushing is assembled in the inner hole of the outer bushing at normal temperature by adopting the outer bushing and the rocker joint and by cold shrinkage of the inner bushing, so that the interference fit between the inner bushing and the outer bushing and the installation coaxiality between the inner holes of the inner bushing in the two mounting holes are ensured to be within a tolerance range.
2. A landing gear rocker joint mounting arrangement based on a self-lubricating bushing as claimed in claim 1, characterised in that the material of the outer and inner bushings is stainless steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711256541.0A CN108082454B (en) | 2017-12-03 | 2017-12-03 | Undercarriage rocker arm joint mounting structure and method based on self-lubricating bushing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711256541.0A CN108082454B (en) | 2017-12-03 | 2017-12-03 | Undercarriage rocker arm joint mounting structure and method based on self-lubricating bushing |
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| Publication Number | Publication Date |
|---|---|
| CN108082454A CN108082454A (en) | 2018-05-29 |
| CN108082454B true CN108082454B (en) | 2022-03-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711256541.0A Active CN108082454B (en) | 2017-12-03 | 2017-12-03 | Undercarriage rocker arm joint mounting structure and method based on self-lubricating bushing |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108916247A (en) * | 2018-08-06 | 2018-11-30 | 浙江长盛塑料轴承技术有限公司 | A kind of automotive seat axis plain bearing unit |
| EP3751160B1 (en) * | 2019-06-14 | 2021-09-15 | Safran Landing Systems UK Limited | Self-lubricating conductive bearing |
| CN111922631B (en) * | 2020-06-28 | 2021-10-15 | 湖北三环锻造有限公司 | Steering knuckle bushing push-free process |
| CN112173072A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Control surface control mechanism of high-speed helicopter |
| CN112412983B (en) * | 2020-11-16 | 2022-05-03 | 贵州贵航飞机设计研究所 | Gap adjusting shaft sleeve for support and rotary rocker arm |
| CN112461526B (en) * | 2020-11-20 | 2022-06-21 | 中国直升机设计研究所 | Fatigue test loading device for main starting rocker arm joint of unmanned helicopter |
| CN118124313A (en) * | 2024-02-04 | 2024-06-04 | 浙江春风动力股份有限公司 | All-terrain vehicle |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2649857Y (en) * | 2003-09-29 | 2004-10-20 | 明基电通股份有限公司 | Combined bush bearing unit |
| CN2837595Y (en) * | 2005-03-13 | 2006-11-15 | 福建龙溪轴承(集团)股份有限公司 | Self-lubricating joint bearing |
| CN201461740U (en) * | 2009-05-11 | 2010-05-12 | 封仪 | Thermometal extrusion bushing |
| CN202991874U (en) * | 2012-12-12 | 2013-06-12 | 浙江博宇机电有限公司 | Wear-proof sleeve of tail shaft of vertical conveyor |
| CN204433045U (en) * | 2014-12-19 | 2015-07-01 | 成都飞机设计研究所 | Compound type self-lubricating rotating cylinder |
| CN204387110U (en) * | 2014-12-19 | 2015-06-10 | 昆山旭祥钣金工业有限公司 | A kind of axle sleeve of rotary axis of machine tool |
| CN204646995U (en) * | 2014-12-25 | 2015-09-16 | 上海市轴承技术研究所 | Self-lubricating bushing joint shaft bearing and helicopter |
| CN204591990U (en) * | 2015-03-18 | 2015-08-26 | 河北省轴承产业技术研究院 | A kind of selflubricating single row conical bearing |
| EP3228539B1 (en) * | 2016-04-06 | 2020-03-04 | Safran Landing Systems UK Limited | Aircraft landing gear assembly |
| CN106812794A (en) * | 2017-03-13 | 2017-06-09 | 浙江双飞无油轴承股份有限公司 | A kind of tandem composite bearing |
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2017
- 2017-12-03 CN CN201711256541.0A patent/CN108082454B/en active Active
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| CN108082454A (en) | 2018-05-29 |
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