CN109606608B - Be used for fuselage wing butt joint structure - Google Patents
Be used for fuselage wing butt joint structure Download PDFInfo
- Publication number
- CN109606608B CN109606608B CN201811466725.4A CN201811466725A CN109606608B CN 109606608 B CN109606608 B CN 109606608B CN 201811466725 A CN201811466725 A CN 201811466725A CN 109606608 B CN109606608 B CN 109606608B
- Authority
- CN
- China
- Prior art keywords
- wing
- joint
- fuselage
- bolt
- cylindrical
- Prior art date
- 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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Links
- 210000001503 joint Anatomy 0.000 title claims abstract description 26
- 238000002955 isolation Methods 0.000 abstract description 4
- 238000010008 shearing Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B13/00—Dowels or other devices fastened in walls or the like by inserting them in holes made therein for that purpose
- F16B13/04—Dowels or other devices fastened in walls or the like by inserting them in holes made therein for that purpose with parts gripping in the hole or behind the reverse side of the wall after inserting from the front
-
- 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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B13/00—Dowels or other devices fastened in walls or the like by inserting them in holes made therein for that purpose
- F16B13/04—Dowels or other devices fastened in walls or the like by inserting them in holes made therein for that purpose with parts gripping in the hole or behind the reverse side of the wall after inserting from the front
- F16B13/10—Dowels or other devices fastened in walls or the like by inserting them in holes made therein for that purpose with parts gripping in the hole or behind the reverse side of the wall after inserting from the front with separate gripping parts moved into their final position in relation to the body of the device by a separate operation
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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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B43/00—Washers or equivalent devices; Other devices for supporting bolt-heads or nuts
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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
Abstract
A butt joint structure for a fuselage and a wing is characterized in that the fuselage joint is connected to the fuselage, a first bushing is in interference fit with the fuselage joint, a wing joint is connected to the wing, and a second bushing is in interference fit with the wing joint; a blind hole for placing a double-cylindrical nut is processed on the wing joint and is vertical to a bolt hole for installing a bolt, and the bolt penetrates through the body joint and is inserted into the wing joint to be matched with the double-cylindrical nut placed in the blind hole to fasten the body joint and the wing joint; the shear bearing bush is arranged on the bolt, the sliding block is positioned between the first bush and the shear bearing bush, the sliding block and the second bush are in clearance fit and are used for protecting the bolt and bearing shearing force; the wing joint is provided with the blind hole due to processing, the structure is provided with a plurality of bulges, but the bulge towards the inside of the wing oil tank saves a lot of space compared with a special space-reserving isolation connecting bolt, and the bolt does not penetrate out of the wing joint, so that oil leakage does not occur at the position with the maximum load and the position with the maximum deformation.
Description
Technical Field
The invention relates to the technical field of mechanical structures, in particular to a butt joint structure for a fuselage and a wing.
Background
The butt joint of the fuselage and the wings is generally realized by respectively arranging butt joints on butt joint surfaces of the fuselage and the wings and connecting the butt joint surfaces by bolts.
For a small airplane, the wing height is low, the wing span is small, and if a wing oil tank is far away from a butt joint, the volume of the oil tank needs to be reduced, so that the wing space is wasted; if the butt joint is fused with the oil tank and a conventional joint structure form is adopted, the sealing requirement of the oil tank cannot be ensured.
Disclosure of Invention
The present invention provides a butt joint structure for fuselage and wing to solve the above-mentioned drawbacks in the background art.
The technical problem solved by the invention is realized by adopting the following technical scheme:
a butt joint structure for a fuselage and a wing comprises a fuselage joint, a first bushing, a wing joint and a second bushing, wherein the fuselage joint is connected to the fuselage, the first bushing is in interference fit with the fuselage joint, the wing joint is connected to the wing, and the second bushing is in interference fit with the wing joint; a blind hole for placing a double-cylindrical nut is processed on the wing joint and is vertical to a bolt hole for installing a bolt, and the bolt penetrates through the body joint and is inserted into the wing joint to be matched with the double-cylindrical nut placed in the blind hole to fasten the body joint and the wing joint; the shear bearing bush is arranged on the bolt, the sliding block is positioned between the first bush and the shear bearing bush, the sliding block and the second bush are in clearance fit and are used for protecting the bolt and bearing shearing force; the wing joint is provided with the blind hole due to the processing, the structure is provided with a plurality of bulges, but the bulge towards the inside of the wing oil tank saves a lot of space compared with a special space isolation connecting bolt, and the bolt does not penetrate through the wing joint, so that oil leakage cannot occur at the maximum load position and the maximum deformation position.
In the invention, the bolt is provided with a washer for protecting the bolt.
In the invention, the inner side of the double-cylindrical nut is provided with the double-cylindrical cushion block.
In the invention, the wing joint is provided with a notch matched with the notch of the second bushing to limit the rotation of the second bushing.
In the invention, the radius of the bi-cylindrical cushion block is equal to the radius of the blind hole.
In the invention, the blind hole is a cylindrical deep hole, a square deep hole or an oval deep hole.
In the invention, the blind hole is a cylindrical deep hole, the double-cylindrical cushion block is provided with a cylindrical surface for being attached to the blind hole, and the double-cylindrical cushion block is attached to the inner cylindrical surface of the deep hole through the cylindrical surface.
In the invention, because the load at the butt joint is very large, the shear bearing bush can be slightly deformed after long working time, and the disassembly is difficult, the shear bearing bush is provided with the notch, so that the disassembly by using a tool is convenient.
Has the advantages that: according to the invention, the blind hole for placing the double-cylindrical-surface nut is processed on the wing joint, and the bolt penetrates through the body joint and is inserted into the wing joint to be matched with the double-cylindrical-surface nut placed in the blind hole to fasten the body joint and the wing joint; the blind hole protrudes towards the inside of the wing oil tank, so that much space is saved compared with a special space isolation connecting bolt, meanwhile, the bolt does not penetrate out of a wing joint, and oil leakage cannot occur at the maximum load position and the maximum deformation position; therefore, the joint in the form can solve the problem of oil leakage of the wing oil tank at the butt joint, and does not waste oil carrying space.
Drawings
FIG. 1 is an assembled elevation view of the preferred embodiment of the present invention.
Fig. 2 is an assembled bottom view of the preferred embodiment of the present invention.
FIG. 3 is a schematic diagram of a dual-cylinder spacer structure according to a preferred embodiment of the present invention.
Fig. 4 is a schematic view of a double-cylinder nut structure in a preferred embodiment of the invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below by combining the specific drawings.
Referring to fig. 1-4, a butt joint structure for a fuselage and a wing comprises a fuselage joint 1, a first bushing 2, a wing joint 3, a second bushing 4, a bolt 5, a shear bearing bushing 6, a gasket 7, a slider 8, a bi-cylindrical cushion block 9, a bi-cylindrical nut 10 and a wing oil tank 11, wherein the fuselage joint 1 is connected to the fuselage, the first bushing 2 is in interference fit with the fuselage joint 1, and the first bushing 2 is limited to rotate by the bolt on the fuselage joint 1; the wing joint 3 is connected to the wing, the second bushing 4 is in interference fit with the wing joint 3, and the second bushing 4 is limited to rotate by the fact that the notch of the wing joint 3 is matched with the notch in the second bushing 4; a blind hole is processed on the wing joint 3, the blind hole is vertical to a bolt hole for mounting the bolt 5, the radius of the blind hole is equal to that of the double-cylindrical cushion block 9, and the double-cylindrical cushion block 9 and the double-cylindrical nut 10 are placed in the blind hole; the bolt 5 is inserted into the wing joint 3 and is matched with the double-cylindrical-surface nut 10 in the blind hole to fasten the fuselage joint 1 and the wing joint 3; the bolt 5 in the structure form can not penetrate through the wing joint 3, and only the upper, lower, front and rear binding surfaces of the wing joint 3 and the wing oil tank 11 are sealed to ensure the local sealing of the joint of the wing oil tank 11 and the wing joint 3; the main load borne by the bolt 5 is shearing force, the washer 7 is used for protecting the bolt 5, and the double-cylindrical cushion block 9 is used for protecting the double-cylindrical nut 10; the shear bearing bush 6 is in clearance fit with the slide block 8 and the second bush 4, and has the function of protecting the bolt 5 and bearing shear force; slider 8 and 2 clearance fit of bush No. one, slider 8 is in bush No. 2 and holds and cut between the bush 6, and the effect makes things convenient for the dismouting.
As shown in figure 1, the wing joint 3 is provided with a plurality of bulges due to the processing of a blind hole for placing a double-cylindrical cushion block 9 and a double-cylindrical nut 10, but the bulge towards the inside of the wing oil tank 11 saves a lot of space compared with a special space isolation connecting bolt, and the bolt 5 does not penetrate through the wing joint 3, so that oil leakage cannot occur at the maximum load position and the maximum deformation position, and the joint in the form can solve the problem of oil leakage of the wing oil tank 11 at the butt joint position and does not waste oil carrying space.
The blind hole is a cylindrical deep hole which is better processed than a square deep hole or an oval deep hole, the double-cylindrical cushion block 9 is provided with a cylindrical surface which is used for being jointed with the blind hole, the double-cylindrical cushion block 9 can be well jointed on the inner cylindrical surface of the cylindrical deep hole through the cylindrical surface to play a limiting role, the double-cylindrical nut 10 can also be well jointed on the double-cylindrical cushion block 9 and can also be limited in position, and the installation of the bolt 5 is convenient; because the load at the butt joint is very large, the shear bearing bush 6 can be slightly deformed after the working time is long, and the disassembly is difficult, the notch is formed in the shear bearing bush 6, and the disassembly by using a tool is convenient.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. A butt joint structure for a fuselage and a wing comprises a fuselage joint, a first bushing, a wing joint and a second bushing, and is characterized in that the fuselage joint is connected to the fuselage, the first bushing is in interference fit with the fuselage joint, the wing joint is connected to the wing, and the second bushing is in interference fit with the wing joint; a blind hole for placing a double-cylindrical nut is processed on the wing joint and is vertical to a bolt hole for installing a bolt, and the bolt penetrates through the body joint and is inserted into the wing joint to be matched with the double-cylindrical nut placed in the blind hole to fasten the body joint and the wing joint; the shear bearing bush is arranged on the bolt, the slide block is positioned between the first bush and the shear bearing bush, and the shear bearing bush is in clearance fit with the slide block and the second bush; meanwhile, the blind holes processed on the wing joints protrude towards the interior of the wing oil tank, so that the space for isolating connecting bolts can be saved; the bolt does not penetrate out of the wing joint, and oil leakage does not occur at the maximum load position, namely the maximum deformation position.
2. The butt joint structure for the fuselage and the wing as claimed in claim 1, wherein the bolt is provided with a washer for protecting the bolt.
3. The butt joint structure for the fuselage and the wing according to claim 1, wherein a bi-cylindrical cushion block is arranged inside the bi-cylindrical nut.
4. The butt joint structure for the fuselage and the wing according to claim 3, wherein the radius of the bi-cylindrical cushion block is equal to the radius of the blind hole.
5. The butt joint structure for the fuselage and the wing according to claim 3, wherein the bi-cylindrical cushion block is provided with a cylindrical surface for fitting with the blind hole.
6. The butt joint structure for the fuselage and the wing as claimed in claim 1, wherein the wing joint is provided with a notch for matching with the notch of the second bushing.
7. The butt joint structure for the fuselage and the wing according to claim 1, wherein the blind hole is a cylindrical deep hole, a square deep hole or an elliptical deep hole.
8. The butt joint structure for the fuselage and the wing as claimed in claim 1, wherein the shear bearing bush has a notch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811466725.4A CN109606608B (en) | 2018-12-03 | 2018-12-03 | Be used for fuselage wing butt joint structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811466725.4A CN109606608B (en) | 2018-12-03 | 2018-12-03 | Be used for fuselage wing butt joint structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109606608A CN109606608A (en) | 2019-04-12 |
| CN109606608B true CN109606608B (en) | 2022-05-31 |
Family
ID=66006960
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811466725.4A Active CN109606608B (en) | 2018-12-03 | 2018-12-03 | Be used for fuselage wing butt joint structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109606608B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101214852A (en) * | 2007-12-28 | 2008-07-09 | 北京航空航天大学 | Connecting structure for unmanned aerial vehicle body and wing |
| CN204937476U (en) * | 2015-08-13 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | The attaching parts of a kind of integral wing tank and external-hanging structure |
| CN207514056U (en) * | 2017-10-20 | 2018-06-19 | 上海大隆机器厂有限公司 | A kind of self-adjustable fastening structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8142126B2 (en) * | 2005-09-02 | 2012-03-27 | The Boeing Company | Multi-piece fastener with self-indexing nut |
-
2018
- 2018-12-03 CN CN201811466725.4A patent/CN109606608B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101214852A (en) * | 2007-12-28 | 2008-07-09 | 北京航空航天大学 | Connecting structure for unmanned aerial vehicle body and wing |
| CN204937476U (en) * | 2015-08-13 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | The attaching parts of a kind of integral wing tank and external-hanging structure |
| CN207514056U (en) * | 2017-10-20 | 2018-06-19 | 上海大隆机器厂有限公司 | A kind of self-adjustable fastening structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109606608A (en) | 2019-04-12 |
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