CN209274873U - A kind of composite joint of embedded bushing component - Google Patents
A kind of composite joint of embedded bushing component Download PDFInfo
- Publication number
- CN209274873U CN209274873U CN201821816191.9U CN201821816191U CN209274873U CN 209274873 U CN209274873 U CN 209274873U CN 201821816191 U CN201821816191 U CN 201821816191U CN 209274873 U CN209274873 U CN 209274873U
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- China
- Prior art keywords
- bushing
- composite joint
- neck bush
- composite
- screw thread
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Abstract
The utility model relates to a kind of composite joints of embedded bushing component, including neck bush (1) and external bushing (2) and composite joint (3), it is characterized by: wherein neck bush (1) is primary load bearing bushing, external bushing (2) and outer surface are equipped with screw thread, the inner surface of neck bush (1) one end is equipped with the screw thread matched with external bushing (2) with outer surface thread, and neck bush (1) and external bushing (2) are pressed by screwing mode in screw thread in the through-hole of composite joint (3).Mode and dimensional fits tolerance are screwed by improving inside and outside bush threads, improves composite joint fatigue properties；More preferable protection composite joint hole wall；It polishes work when eliminating bushing press-mounting；When connector docks bushing fraising, guarantee that primary load bearing bush threads end wall is thick.
Description
Technical field
The utility model belongs to airplane structural design technology, and in particular to a kind of composite material of embedded bushing component connects
Head.
Background technique
Composite joint needs embedded metal bushing to protect composite material hole wall, mentions as aircraft primary load bearing component
High composite joint fatigue properties.Composite joint embedded bushing is essentially outward turning mode at present, and which feature is lining
Set and multiple material hole wall binding face are few；Due to the easy super thick characteristic of multiple material part thickness, needed before bushing press-mounting according to connector actual (real) thickness by
Batch polishing；When connector docks bushing fraising, it is thick to will affect primary load bearing bush threads end wall.
Summary of the invention
Goal of the invention: a kind of composite joint design scheme of embedded bushing component is proposed.
Technical solution: a kind of composite joint of embedded bushing component, including neck bush 1 and external bushing 2 and composite wood
Expect connector 3, wherein neck bush 1 is primary load bearing bushing, and external bushing 2 and outer surface are equipped with screw thread, on the inner surface of 1 one end of neck bush
Equipped with the screw thread matched with external bushing 2 with outer surface thread, neck bush 1 is pressed with external bushing 2 by screwing mode in screw thread
In in the through-hole of composite joint 3.
1 total length of neck bush is identical as non-threaded segment length tolerance, and the margin of tolerance is 0~-0.02mm.External bushing
2 thread segment length tolerance ranges are 0~-0.02mm.The neck bush 1 is with 3 matching allowance range of composite joint
0.02mm~0.06mm.
Neck bush 1 and external bushing 2 are made of the metal of identical material.Neck bush 1 and external bushing 2 are machined piece,
Composite joint 3 is composite product.
Invention advantage: mode and dimensional fits tolerance are screwed by improving inside and outside bush threads, improves composite joint
Fatigue properties；More preferable protection composite joint hole wall；It polishes work when eliminating bushing press-mounting；When connector docks bushing fraising,
Guarantee that primary load bearing bush threads end wall is thick.
Detailed description of the invention
Fig. 1 is the utility model structure sectional view.
Specific embodiment
As shown in Figure 1, a kind of composite joint of embedded bushing component, including neck bush 1 and external bushing 2 and composite wood
Expect connector 3, wherein neck bush 1 is primary load bearing bushing, and external bushing 2 and outer surface are equipped with screw thread, on the inner surface of 1 one end of neck bush
Equipped with the screw thread matched with external bushing 2 with outer surface thread, the press fitting of neck bush 1 is in the through-hole hole of composite joint 3, outside
Bushing 2 and neck bush 1 carry out screwing assembling.
1 total length of neck bush is identical as non-threaded segment length tolerance, and the margin of tolerance is 0~-0.02mm.External bushing
2 thread segment length tolerance ranges are 0~-0.02mm.The neck bush 1 is with 3 matching allowance range of composite joint
0.02mm~0.06mm.
Neck bush 1 and external bushing 2 are made of the metal of identical material.Neck bush 1 and external bushing 2 are machined piece,
Composite joint 3 is composite product.
Compared with prior art, the utility model has the advantages that the following:
1. improving composite joint fatigue properties；
2. more preferably protection composite joint hole wall；
3. work of polishing when elimination bushing press-mounting；
4. connector docks bushing fraising, guarantee primary load bearing bush threads end wall thickness etc..
Claims (6)
1. a kind of composite joint of embedded bushing component, including neck bush (1) and external bushing (2) and composite joint
(3), it is characterised in that: wherein neck bush (1) is primary load bearing bushing, and external bushing (2) and outer surface are equipped with screw thread, neck bush (1)
The inner surface of one end is equipped with the screw thread matched with external bushing (2) with outer surface thread, and neck bush (1) and external bushing (2) are logical
The mode that screws is crossed in screw thread to be pressed in the through-hole of composite joint (3).
2. the composite joint of embedded bushing component according to claim 1, which is characterized in that the neck bush (1)
Total length is identical as non-threaded segment length tolerance, and the margin of tolerance is 0~-0.02mm.
3. the composite joint of embedded bushing component according to claim 1, which is characterized in that external bushing (2) screw thread
The segment length margin of tolerance is 0~-0.02mm.
4. the composite joint of embedded bushing component according to claim 1, which is characterized in that the neck bush (1)
It is 0.02mm~0.06mm with composite joint (3) matching allowance range.
5. the composite joint of embedded bushing component according to claim 1, which is characterized in that neck bush (1) and outer
Bushing (2) is made of same metal material.
6. the composite joint of embedded bushing component according to claim 1, which is characterized in that neck bush (1) and outer
Bushing (2) is machined piece, and composite joint (3) is composite product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821816191.9U CN209274873U (en) | 2018-11-05 | 2018-11-05 | A kind of composite joint of embedded bushing component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821816191.9U CN209274873U (en) | 2018-11-05 | 2018-11-05 | A kind of composite joint of embedded bushing component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209274873U true CN209274873U (en) | 2019-08-20 |
Family
ID=67600531
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821816191.9U Active CN209274873U (en) | 2018-11-05 | 2018-11-05 | A kind of composite joint of embedded bushing component |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209274873U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112549381A (en) * | 2020-10-30 | 2021-03-26 | 哈尔滨飞机工业集团有限责任公司 | Detachable lining assembly of composite material mold and mounting and replacing method |
| CN113697099A (en) * | 2021-06-11 | 2021-11-26 | 昌河飞机工业（集团）有限责任公司 | Repairing structure and method for damaged inner surface of helicopter root bushing |
-
2018
- 2018-11-05 CN CN201821816191.9U patent/CN209274873U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112549381A (en) * | 2020-10-30 | 2021-03-26 | 哈尔滨飞机工业集团有限责任公司 | Detachable lining assembly of composite material mold and mounting and replacing method |
| CN113697099A (en) * | 2021-06-11 | 2021-11-26 | 昌河飞机工业（集团）有限责任公司 | Repairing structure and method for damaged inner surface of helicopter root bushing |
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