CN214641577U - Tool for assembling aviation case plug - Google Patents
Tool for assembling aviation case plug Download PDFInfo
- Publication number
- CN214641577U CN214641577U CN202120356349.4U CN202120356349U CN214641577U CN 214641577 U CN214641577 U CN 214641577U CN 202120356349 U CN202120356349 U CN 202120356349U CN 214641577 U CN214641577 U CN 214641577U
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- guide
- hole
- guide hole
- plug
- guide part
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Abstract
The utility model belongs to aviation machine casket assembly field, concretely relates to frock for assembly of aviation machine casket end cap. The method comprises the following steps: the guide rod comprises a first guide part and a second guide part, wherein the first guide part is in clearance fit with the first guide hole, the second guide part is in clearance fit with the second guide hole, and the length of the first guide part is greater than the depth of the first guide hole. The pressure assembly can be carried out under the condition of guidance, the shaft diameter of the plug is ensured to be superposed with the shaft diameter of the oil way hole, and the reliability of the plug assembly is realized.
Description
Technical Field
The utility model belongs to aviation machine casket assembly field, concretely relates to frock for assembly of aviation machine casket end cap.
Background
A large number of oil way holes are formed in the aviation case, plugs are required to be assembled in oil way holes to guarantee the sealing performance of an oil way, the plugs and the oil way holes are in interference fit, and tools such as hand hammers are required to be used for pressure assembly. During assembly, the reliability of assembly can be guaranteed only when the overlap ratio of the plug and the aperture axis is high, otherwise, the oil leakage phenomenon is easy to occur, and the product quality is affected. The traditional assembly mode is only guided by the chamfers of the plug and the oil way orifice and is unreliable, the condition that the tightness is unqualified after assembly often occurs, a novel assembly tool with a guide sleeve is designed, and the assembly tool is very important for improving the assembly quality of the plug.
Disclosure of Invention
Utility model purpose: the tool for assembling the aviation case plug is used for performing pressure assembly under the condition of guidance, so that the shaft diameter of the plug is ensured to be overlapped with the shaft diameter of an oil way hole, and the reliability of plug assembly is realized.
The technical scheme is as follows:
in a first aspect, a tooling for assembling an aviation casing plug is provided, which includes: the guide rod comprises a first guide part and a second guide part, wherein the first guide part is in clearance fit with the first guide hole, the second guide part is in clearance fit with the second guide hole, and the length of the first guide part is greater than the depth of the first guide hole.
Further, still include stop screw, wherein the second guide portion outside is provided with spacing recess, and the guide housing outside is provided with the screw hole, and the screw passes the spacing groove of screw hole and second guide portion for it is spacing to carry out the axial to the depression bar.
Further, the length of the first guide part is greater than the depth of the first guide hole, and the first guide part specifically comprises: the length of the first guide part is not less than the sum of the depth of the first guide hole and the depth of the plug recess.
Furthermore, the verticality requirement of the first guide hole of the guide sleeve and the end face of the first guide hole is not more than 0.02mm, and the plug is guaranteed to be perpendicular to the end face after being assembled.
Furthermore, the outer diameter of one end of the guide sleeve is smaller than that of the other end of the guide sleeve, so that interference with other parts in the installation process of the plug is avoided.
Furthermore, the compression bar is a steel compression bar.
Has the advantages that: the utility model discloses the novel assembly fixture who well adopts, simple structure, convenient and practical, low cost can carry out pressure assembly under the condition that has the guide, guarantees the axle footpath of end cap and the axle footpath coincidence in oil circuit hole, has realized the reliability of end cap assembly.
Drawings
Fig. 1 is a general schematic diagram of a frock for aviation case end cap assembly according to the utility model discloses an embodiment:
fig. 2 is according to the utility model discloses end cap pre-installation schematic diagram:
fig. 3 is a schematic view of the plug assembly according to the embodiment of the present invention:
wherein: 1-guide sleeve, 2-pressure bar, 3-limit screw.
Detailed Description
According to the utility model discloses a frock for assembly of aviation machine casket end cap, as shown in fig. 1, constitute by guide pin bushing 1, depression bar 2, stop screw 3 triplex, there are two in the middle of the guide pin bushing 1 and depression bar matched with hole and one and stop screw complex screw hole, still have a department's rectangular groove in the guide pin bushing 1, play limiting displacement with stop screw 3 cooperation. The verticality requirement of the end face of the guide sleeve 1 and the aperture is not more than 0.02mm, the end face is perpendicular to the end face after the plug is assembled, and the axis diameter of the plug is coincident with the axis diameter of the oil way hole after the end face is attached to the assembly surface of the part. The clearance between the aperture of the guide sleeve 1 and the plug is 0.01-0.03mm, the pressure rod 2 protrudes out of the surface of the guide sleeve 1 at the limit position on the left side, the plug is required to be lower than the mounting surface after being assembled, and the distance B is equal to the size of the plug which is lower than the mounting plane after being assembled. The guide sleeve 1, the compression bar 2 and the limit screw 3 are all made of steel.
The working principle is as follows:
as shown in fig. 2 to 3, the plug is firstly placed in the guide sleeve 1, then the pressure lever 2 is completely attached to the end face of the oil path hole of the casing, the position is determined by the chamfer angle between the plug and the oil path hole, the pressure lever 2 is manually pressed, the pressure lever 2 is knocked by a hand hammer, the plug is pressed into the oil path hole, and the size of the plug lower than the mounting surface of the casing is ensured by the distance of the pressure lever 2 protruding out of the end face of the guide sleeve 1. Because the guide sleeve 1 is used as a guide in the pressure loading process, and the fit clearance between the plug and the aperture of the guide sleeve 1 is small, the shaft diameter of the plug can be ensured to be coincident with the shaft diameter of the oil way hole of the casing, the assembly relation is ensured, and the oil leakage fault is avoided.
Claims (6)
1. The utility model provides a frock for aviation case end cap assembly which characterized in that includes: the guide rod comprises a guide sleeve (1) and a pressure rod (2), wherein one end of the guide sleeve (1) is provided with a first guide hole, the other end of the guide sleeve (1) is provided with a second guide hole, the first guide hole is coaxially communicated with the second guide hole, the inner diameter of the first guide hole is smaller than that of the second guide hole, the inner diameter of the first guide hole is 0.01mm to 0.03mm larger than the outer diameter of a plug, the guide rod comprises a first guide part and a second guide part, the first guide part is in clearance fit with the first guide hole, the second guide part is in clearance fit with the second guide hole, and the length of the first guide part is larger than the depth of the first guide hole.
2. The tool according to claim 1, further comprising a limiting screw (3), wherein a limiting groove is formed in the outer side of the second guide portion, a screw hole is formed in the outer side of the guide sleeve (1), and the screw penetrates through the screw hole and the limiting groove of the second guide portion and is used for axially limiting the compression bar (2).
3. The tooling of claim 1, wherein the length of the first guide part is greater than the depth of the first guide hole, and the tooling specifically comprises:
the length of the first guide part is not less than the sum of the depth of the first guide hole and the depth of the plug recess.
4. The tooling of claim 1, wherein the perpendicularity requirement of the first guide hole of the guide sleeve (1) and the end face of the first guide hole is not more than 0.02mm, so that the end cap is perpendicular to the end face after being assembled.
5. The tooling of claim 1, wherein the outer diameter of one end of the guide sleeve (1) is smaller than that of the other end thereof, so as to prevent the interference with other parts in the installation process of the plug.
6. The tooling according to claim 1, characterized in that the press rod (2) is a steel press rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120356349.4U CN214641577U (en) | 2021-02-09 | 2021-02-09 | Tool for assembling aviation case plug |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120356349.4U CN214641577U (en) | 2021-02-09 | 2021-02-09 | Tool for assembling aviation case plug |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214641577U true CN214641577U (en) | 2021-11-09 |
Family
ID=78447231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120356349.4U Active CN214641577U (en) | 2021-02-09 | 2021-02-09 | Tool for assembling aviation case plug |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214641577U (en) |
-
2021
- 2021-02-09 CN CN202120356349.4U patent/CN214641577U/en active Active
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