CN209180209U - A kind of combination bushing for the compensation of aircaft configuration single side link bolt hole - Google Patents
A kind of combination bushing for the compensation of aircaft configuration single side link bolt hole Download PDFInfo
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- CN209180209U CN209180209U CN201822120504.3U CN201822120504U CN209180209U CN 209180209 U CN209180209 U CN 209180209U CN 201822120504 U CN201822120504 U CN 201822120504U CN 209180209 U CN209180209 U CN 209180209U
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- bushing
- plate nut
- hole
- liner body
- rivet
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Abstract
The utility model discloses a kind of combination bushings for the compensation of aircaft configuration single side link bolt hole, it include bushing, plate nut and rivet, the bushing include liner body and be set to liner body periphery and with the integrally formed convex shoulder of liner body, multiple riveted holes to match with rivet are equipped in convex shoulder and plate nut, corresponding riveted holes are passed through by rivet between bushing and plate nut, realizes and is fixedly connected between bushing and plate nut；It is equipped with through-hole up and down at the center of liner body, the threaded hole with the concentric setting of through-hole is equipped in plate nut, structure and the through-hole of threaded hole match.The connection bolt of former specification can still be installed after compensating by combination bushing using combination bushing described in the utility model in situ.Simple with structure, easy for installation, stability is good, is suitble to promote and apply.
Description
Technical field
The utility model relates to aeroplane structure design and service technique fields, and in particular to one kind is used for aircaft configuration single side
The combination bushing of link bolt hole compensation.
Background technique
For aircraft during assembly, detachable structure component is generally used a large amount of monaural, ears, butterfly supporting plate spiral shell
Female gasket compensates connection, and plate nut is fixed on skeleton, is screwed by bolt from the skin-surface of aircraft, with this into
Row is connected and fixed covering, and plate nut is a kind of aircraft fit on commonly aircraft single side connection structure form.Due to the connection
Form, which is mainly concerned with, to be needed to carry out drilling on skeleton, assemble plate nut with this, pilot hole on covering.Actually make
With the hole that in the process, often will appear on skeleton on hole and covering, occur not the same axle center the problem of or on skeleton
Hole occurs the factors such as impaired and causes unqualified situation.After progress reaming is remedied, and it can bring since bolt increases, load transmission
It changes and the problems such as large-sized bolt surface structure is unable to satisfy its countersunk head requirement.Therefore, it is necessary to design a kind of knot
Structure is simple, easy for installation, the good compensation attachment device of stability.
Utility model content
The problem of the technical problems to be solved in the utility model is for background technique provides a kind of structure letter
Single, easy for installation, the good compensation attachment device of stability is specifically a kind of to mend for aircaft configuration single side link bolt hole
The combination bushing repaid.
It is compensated in order to solve the above technical problems, the utility model provides one kind for aircaft configuration single side link bolt hole
Combination bushing, include bushing, plate nut and rivet, the bushing includes liner body and is set to liner body periphery
And with the integrally formed convex shoulder of liner body, be equipped with and multiple match with the rivet in the convex shoulder and plate nut
Riveted holes pass through corresponding riveted holes by rivet between the bushing and plate nut, realize the bushing and plate nut
Between be fixedly connected；It is equipped with through-hole up and down at the center of the liner body, is equipped with and institute in the plate nut
The threaded hole of the concentric setting of through-hole is stated, the structure of the threaded hole matches with the through-hole.
Further, a kind of combination lining for the compensation of aircaft configuration single side link bolt hole described in the utility model
Set, wherein being all provided in the convex shoulder and plate nut there are two riveted holes, two riveted holes are in symmetry status distribution；Institute
It states and is additionally provided with multiple connecting holes in convex shoulder, multiple connecting holes are located on the outside of riveted holes, and are distributed in the convex shoulder in symmetry status
In.
Further, a kind of combination lining for the compensation of aircaft configuration single side link bolt hole described in the utility model
Set, wherein the plate nut is monaural plate nut, ears plate nut or angular plate nut structure.
It is and existing using a kind of combination bushing for the compensation of aircaft configuration single side link bolt hole described in the utility model
There is technology to compare, advantageous effects are as follows: multiple with the rivet phase due to being equipped in the convex shoulder and plate nut
Matched riveted holes pass through corresponding riveted holes by rivet between the bushing and plate nut, realize the bushing and support
It is fixedly connected between crab bolt；In addition, through-hole up and down is equipped at the middle part of the liner body, in the plate nut
In be equipped with threaded hole with the concentric setting of the through-hole, the structure of the threaded hole matches with the through-hole.By to spiral shell
The single side link bolt hole of the underproof structural member of keyhole is reamed, after reaming correction, then is pressed into described in the utility model
Bushing is combined, and is riveted using external rivet, realizes that it is fixedly connected, to reach the effect of being connected and fixed.Using this reality
With the novel combination bushing, can solve aircaft configuration single side connect link bolt hole it is unqualified after ream, can bring
It increases the diameter of bolt and causes load transfer；Aircraft surfaces structure is connected using countersunk head, is not able to satisfy countersunk head after increasing connection bolt
It is required that etc. unfavorable factors the connection bolt of former specification can be still installed in situ by combining after bushing compensates.With structure
Simply, easy for installation, stability is good, is suitble to promote and apply.
Detailed description of the invention
The utility model is described in further detail with reference to the accompanying drawing.
Fig. 1 is the structural schematic diagram of the utility model；
Fig. 2 is scheme of installation when the utility model is used.
Shown in attached drawing: 1- bushing, 11- liner body, 12- convex shoulder, 2- plate nut, 3- rivet, 4- through-hole, 5- screw thread
Hole, the underproof structural member of 6- bolt hole, 7- surface texture, 8- connection bolt, the outside 9- rivet.
Specific embodiment
The principles of the present invention and structure feature are described below in conjunction with attached drawing, example is served only for explaining real
With novel, it is not intended to limit the scope of the utility model.
As shown in Figure 1, a kind of combination lining for the compensation of aircaft configuration single side link bolt hole described in the utility model
Set, includes bushing 1, plate nut 2 and rivet 3, and the bushing 1 includes liner body 11 and is set to 11 periphery of liner body
And with the integrally formed convex shoulder 12 of liner body 11, be equipped in the convex shoulder 12 and plate nut 2 multiple with the rivet 3
The riveted holes to match pass through corresponding riveted holes by rivet 3 between the bushing 1 and plate nut 2, realize the bushing
It is fixedly connected between 1 and plate nut 2；It is equipped with through-hole 4 up and down at the center of the liner body 11, in the supporting plate
The threaded hole 5 with the concentric setting of the through-hole 4 is equipped in nut 2, the structure of the threaded hole 5 matches with the through-hole 4.
Further, a kind of combination lining for the compensation of aircaft configuration single side link bolt hole described in the utility model
Set, wherein being all provided in the convex shoulder 12 and plate nut 2 there are two riveted holes, two riveted holes are in symmetry status distribution；
Multiple connecting holes are additionally provided in the convex shoulder 12, multiple connecting holes are located on the outside of riveted holes, and are distributed in institute in symmetry status
It states in convex shoulder 12.By set connecting hole, it can be used for being riveted with external rivet 9, realize that it is fixedly connected.
Further, a kind of combination lining for the compensation of aircaft configuration single side link bolt hole described in the utility model
Set, wherein the plate nut 2 is monaural plate nut, ears plate nut or angular plate nut structure.
As shown in Fig. 2, in actual application, using described in the utility model a kind of for aircaft configuration single side company
The combination bushing of connecting bolt hole compensation, its working principle is that: phase will be passed through by rivet 3 between bushing 1 and plate nut 2 first
The riveted holes answered are realized and are fixedly connected between bushing 1 and plate nut 2, so that combination bushing described in the utility model is formed,
After carrying out reaming or fraising to the underproof structural member of bolt hole 6, indentation combination bushing, and institute is passed through by external rivet 9
It states connecting hole to be fixedly connected, be then equipped with using connection bolt 8 from the middle part that surface texture 7 enters liner body 11
In through-hole 4, finally it is spirally connected with the threaded hole 5 in the plate nut 2.When by the underproof structural member of bolt hole 6
Single side link bolt hole reamed, after reaming correction, be pressed into combination bushing described in the utility model, and use external riveting
Nail 9 is riveted, and realizes that it is fixedly connected, to reach the effect of being connected and fixed.
In conclusion can solve aircaft configuration single side connecting bolt in succession using combination bushing described in the utility model
It reams after hole is unqualified, the increasing diameter of bolt can be brought to cause load transfer；Aircraft surfaces structure is connected using countersunk head, is added
The unfavorable factors such as countersunk head requirement are not able to satisfy after the connecting bolt of Dalian, after being compensated by combination bushing, can still be installed in situ
The connection bolt of former specification.Simple with structure, easy for installation, stability is good, is suitble to promote and apply.
Above description is merely a prefered embodiment of the utility model, is not intended to limit the utility model, for ability
For the technical staff in domain, there can be various modifications and variations, it is all to utilize any modification made by the utility model, equally replace
It changes, improve, should be included within the scope of protection of this utility model.
Claims (3)
1. it is a kind of for aircaft configuration single side link bolt hole compensation combination bushing, it is characterised in that: include bushing (1),
Plate nut (2) and rivet (3), the bushing (1) include liner body (11) and be set to liner body (11) periphery and with
Liner body (11) integrally formed convex shoulder (12), be equipped in the convex shoulder (12) and plate nut (2) it is multiple with it is described
The riveted holes that rivet (3) matches pass through corresponding riveting by rivet (3) between the bushing (1) and plate nut (2)
Hole is realized and is fixedly connected between the bushing (1) and plate nut (2)；It is equipped with up and down at the center of the liner body (11)
The through-hole (4) of perforation is equipped with the threaded hole (5) with the through-hole (4) concentric setting in the plate nut (2), described
The structure of threaded hole (5) matches with the through-hole (4).
2. a kind of combination bushing for the compensation of aircaft configuration single side link bolt hole according to claim 1, feature
It is: is all provided in the convex shoulder (12) and plate nut (2) there are two riveted holes, two riveted holes divide in symmetry status
Cloth；Multiple connecting holes are additionally provided in the convex shoulder (12), multiple connecting holes are located on the outside of riveted holes, and are distributed in symmetry status
In the convex shoulder (12).
3. a kind of combination bushing for the compensation of aircaft configuration single side link bolt hole according to claim 1, feature
Be: the plate nut (2) is monaural plate nut, ears plate nut or angular plate nut structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822120504.3U CN209180209U (en) | 2018-12-18 | 2018-12-18 | A kind of combination bushing for the compensation of aircaft configuration single side link bolt hole |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822120504.3U CN209180209U (en) | 2018-12-18 | 2018-12-18 | A kind of combination bushing for the compensation of aircaft configuration single side link bolt hole |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209180209U true CN209180209U (en) | 2019-07-30 |
Family
ID=67377194
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822120504.3U Active CN209180209U (en) | 2018-12-18 | 2018-12-18 | A kind of combination bushing for the compensation of aircaft configuration single side link bolt hole |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209180209U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112628252A (en) * | 2020-12-28 | 2021-04-09 | 中国航发沈阳发动机研究所 | Connecting assembly and connecting structure thereof |
-
2018
- 2018-12-18 CN CN201822120504.3U patent/CN209180209U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112628252A (en) * | 2020-12-28 | 2021-04-09 | 中国航发沈阳发动机研究所 | Connecting assembly and connecting structure thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 561000 Anshun economic and Technological Development Zone, Guizhou Patentee after: Guizhou Guifei aircraft design and Research Institute Co.,Ltd. Address before: 561000 Anshun economic and Technological Development Zone, Guizhou Patentee before: GUIZHOU AVIATION AIRCRAFT DESIGN INSTITUTE |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230628 Address after: 561000 Songqi Town, Anshun economic and Technological Development Zone, Guizhou Province Patentee after: AVIC GUIZHOU AIRPLANE Co.,Ltd. Address before: 561000 Anshun economic and Technological Development Zone, Guizhou Patentee before: Guizhou Guifei aircraft design and Research Institute Co.,Ltd. |