CN108032052A - Fuselage wallboard assembly jig of the cross section radian more than π and its removal method - Google Patents
Fuselage wallboard assembly jig of the cross section radian more than π and its removal method Download PDFInfo
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- CN108032052A CN108032052A CN201711309994.5A CN201711309994A CN108032052A CN 108032052 A CN108032052 A CN 108032052A CN 201711309994 A CN201711309994 A CN 201711309994A CN 108032052 A CN108032052 A CN 108032052A
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- China
- Prior art keywords
- fuselage wallboard
- fuselage
- loop bar
- cross
- wallboard
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Classifications
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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
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H1/00—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby
- B25H1/06—Work benches; Portable stands or supports for positioning portable tools or work to be operated on thereby of trestle type
-
- 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
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Conveying And Assembling Of Building Elements In Situ (AREA)
Abstract
The invention discloses a kind of fuselage wallboard assembly jig of cross section radian more than π and its remove method, belong to aircraft mounting technology field, a kind of assembly jig for the fuselage wallboard assembling that π is relatively larger than for cross section radian is provided, fuselage wallboard is removed in order to facilitate after mounting.The assembly jig, including may be disposed inside fuselage wallboard and be used to support the type frame main body of fuselage wallboard, when assembling fuselage wallboard, the outer contour of the type frame main body is to being reserved with certain interval between fuselage wallboard；Supporting mechanism is provided with the gap, the supporting mechanism includes mounting base, loop bar and positioning pin；The installing plate with the L-shaped distribution of loop bar is provided with one end of loop bar, the installing plate is used to be connected with fuselage wallboard.The present invention can easily realize after the completion of fuselage wallboard assembling and be smoothly moved out fuselage wallboard of the cross section radian more than π from assembly jig.
Description
Technical field
The present invention relates to aircraft mounting technology field, more particularly to a kind of fuselage wallboard of cross section radian more than π to fill
Removal method with type frame and after the completion of fuselage wallboard assembling.
Background technology
Usually when assembling fuselage wallboard, the assembly jig of fuselage wallboard is all located on the inside of siding, and main cause has two：1、
It is smooth and relatively continuous skin-surface on the outside of aircraft panel, and the main force transferring structure of siding, such as frame, beam and stringer
Structure；It is respectively positioned on the inside of covering, assembly jig is placed on the inside of siding, it is convenient to which it is fixed to be selected on the main force transferring structure of siding
Position benchmark, supporting structure, are also more convenient for setting the mechanisms such as locator, supporter on assembly jig；2nd, for same siding,
Internal assembly jig assembly jig all far smaller than exterior in volume and complex degree of structure, reaches for length, width and height size
Several meters, also to ensure for the assembly jig of enough rigidity, it is all extremely significant to reduce volume and complexity.
For cross section radian less than or equal to π fuselage wallboard for, siding be not easy when being removed from assembly jig by
Stop, therefore it is very convenient to remove process；But for cross section radian is relatively larger than the fuselage wallboard of π, siding is from assembling
Easily with the mechanical interferences such as the locator on assembly jig, supporter, and then the removal of fuselage wallboard will be led when being removed in type frame
Process is very inconvenient, and misoperation is also easy to cause wounding, damaging for fuselage wallboard；Cause serious economic loss.
The content of the invention
The technical problem to be solved by the present invention is to provide a kind of fuselage wallboard assembling that π is relatively larger than for cross section radian
Assembly jig, fuselage wallboard is removed in order to facilitate after mounting.
The technical solution adopted by the present invention to solve the technical problems is：Fuselage wallboard of the cross section radian more than π fills
With type frame, including it may be disposed inside fuselage wallboard and be used to support the type frame main body of fuselage wallboard, when assembling fuselage wallboard,
The outer contour of the type frame main body is to being reserved with certain interval between fuselage wallboard；Supporting mechanism is provided with the gap,
The supporting mechanism is installed in the circumferential profile of type frame main body, and the supporting mechanism includes mounting base, loop bar and positioning pin, peace
Dress seat is fixedly installed in type frame main body, axial set is provided with mounting base, the loop bar is arranged in axial set, and is covered
Bar is installed by dismountable positioning pin, and after positioning pin is dismantled, the loop bar at least can axially be freely rotated in set；
The installing plate with the L-shaped distribution of loop bar is provided with one end of loop bar, the installing plate is used to be connected with fuselage wallboard.
It is further：The width in the gap is 100mm~500mm.
It is further：After positioning pin is dismantled, the loop bar is axially also being axially movable in set.
It is further：The loop bar is to be removably disposed in axial set.
It is further：Grid beam is provided with the inside of fuselage wallboard, the installing plate is connected with the grid beam of correspondence position
Connect.
In addition, the present invention also provides a kind of removal method of fuselage wallboard of cross section radian more than π, it uses above-mentioned
Cross section radian described in invention is more than the fuselage wallboard assembly jig of π, after in fuselage wallboard, installation is complete, according to as follows
Step carries out：
The first step：Prepare before removing：Supporting suspender is sling with row, suspender is connected and fixed with fuselage wallboard；
Remove the connection between fuselage wallboard and installing plate；
Second step：Adjust loop bar position：Positioning pin is removed, then rotating loop bar makes installing plate in the vertical of fuselage wallboard entirety
Stagger to direction and fuselage wallboard；
3rd step：Fuselage wallboard is integrally moved up to certain distance L 1；
4th step：Fuselage wallboard is overall to its heading translation certain distance L 2；
5th step：Fuselage wallboard is integrally sling upwards and is removed from assembly jig.
It is further：：In the third step, its displacement distance L1 is 10mm；In the 4th step, its displacement distance L2 is
150mm。
It is further：In the first step, while siding is tied down from all directions using more soft long ropes and outwards led
Draw, and every rope is drawn by an operating personnel；Pass through the traction to rope in afterwards to fuselage wallboard moving process
To reduce rocking for fuselage wallboard.
It is further：In second step, loop bar is removed together with installing plate after removing positioning pin.
The beneficial effects of the invention are as follows：The present invention manufactures and designs without additional dedicated again is used for the large-scale of fuselage wallboard removal
Equipment, without the splicing structure that assembly jig is made to polylith, only with the assembly jig of conventional structure and supporting corresponding
Supporting mechanism is supported, while by matching corresponding suspender, going and hang, you can easily in fuselage wall
Realized after the completion of plate assembling and be smoothly moved out fuselage wallboard of the cross section radian more than π from assembly jig.
Brief description of the drawings
Fig. 1 is schematic perspective view of the assembly jig of the present invention when assembling fuselage wallboard；
Fig. 2 is the front view of Fig. 1；
Fig. 3 is the top view of Fig. 1；
Fig. 4 is the schematic perspective view of assembly jig；
Fig. 5 is the front view of Fig. 4；
Fig. 6 is the schematic diagram of the partial sector A intercepted in Fig. 2；
Fig. 7 is the schematic perspective view of Fig. 6；
Fig. 8 is that the anti-of regional area B in Fig. 7 plays schematic diagram；
Fig. 9 is that the schematic diagram behind fuselage wallboard part is hidden in Fig. 7；
Figure 10, Figure 11 are respectively the schematic perspective view of supporting mechanism under different angle；
Figure 12 is cross-sectional view when coordinating between fuselage wallboard of the cross section radian more than π and assembly jig；
In figure mark for：Fuselage wallboard 1, type frame main body 2, grid beam 3, supporting mechanism 4, mounting base 41, loop bar 42, positioning pin
43rd, axial set 44, installing plate 45, gap 5, cushion block 6.
Embodiment
The present invention is further described with reference to the accompanying drawings and detailed description.
As shown in Figure 12, heretofore described cross section radian is more than the fuselage wallboard 1 of π, it is referred to from fuselage
Observed on the cross section of siding 1, its span exceedes 180 degree, i.e., in more than half arc-shaped structure, accordingly in fuselage wallboard 1
Bottom have less opening, structure as shown in Figure 12.In this case, the assembling inside fuselage wallboard 1
The overall bottom opening that will necessarily be more than fuselage wallboard 1 in a vertical direction of type frame；Therefore cannot directly be used after the completion of assembling
Suspender, row, which are hung etc., to be sling the fuselage wallboard 1 after assembling and removes upwards.
As shown in attached drawing 1 to Figure 11, heretofore described cross section radian is more than the fuselage wallboard assembly type of π
Frame, including may be disposed at the inside of fuselage wallboard 1 and be used to support the type frame main body 2 of fuselage wallboard 1, when assembling fuselage wallboard 1,
The outer contour of the type frame main body 2 is to being reserved with certain interval 5 between fuselage wallboard；Support machine is provided with the gap 5
Structure 4, the supporting mechanism 4 are installed in the circumferential profile of type frame main body 2, and the supporting mechanism 4 includes mounting base 41, loop bar 42
With positioning pin 43, mounting base 41 is fixedly installed in type frame main body 2, and axial set 44, the loop bar are provided with mounting base 41
42 are arranged in axial set 44, and loop bar 42 is installed by dismountable positioning pin 43, after positioning pin 43 are dismantled, institute
State loop bar 42 at least can axially be freely rotated in set 44；The peace with 42 L-shaped distribution of loop bar is provided with one end of loop bar 42
Loading board 45, the installing plate 45 are used to be connected with fuselage wallboard 1.
Wherein, type frame main body 2 is generally in frame structure, and such as attached drawing 4, shown in 5, and the outer contour of type frame main body 2 should
When being substantially mutually matched with fuselage wallboard 1, while it should also meet that in a vertical direction, the width of type frame main body 2 should be less than
The bottom opening of fuselage wallboard 1, could so allow fuselage wallboard 1 subsequently is sling removal upwards.Certainly, in such situation
Under, corresponding gap 5 will necessarily be formed between fuselage wallboard 1 and type frame main body 2；Therefore need the installation in gap 5 suitable
Supporting mechanism 4, to realize support to fuselage wallboard 1.Without loss of generality, may be used also between supporting mechanism 4 and type frame main body 2
Cushion block 6 after being set accordingly according to specific size pad, so that the supporting mechanism 4 after installation can effectively support fuselage wallboard 1.
Referring to the drawings shown in 10 and 11, the supporting mechanism 4 in the present invention, it specifically includes mounting base 41, loop bar 42, determines
Position pin 43, the axial set structure such as 44 and installing plate 45.In this way, when needing to support fuselage wallboard 1, can be incited somebody to action by positioning pin 43
Loop bar 42 is fixedly mounted in mounting base 41, and installing plate 45 should be stretched out towards 1 side of fuselage wallboard at this time, and then can be passed through
Installing plate 45 realizes the supporting role to fuselage wallboard 1.And when after the completion of assembling, it is necessary to when removing fuselage wallboard 1, then by tearing open
After unloading positioning pin 43, it can be made by rotating or dismantling loop bar 42 between installing plate 45 and fuselage wallboard in longitudinal direction and perpendicular
A determining deviation is flowed out to direction, to allow fuselage wallboard 1 to sling upwards, while allows fuselage wallboard 1 opposite in longitudinal direction
Moved a certain distance in assembly jig.Wherein, longitudinal direction described above, refers to the overall axis direction of fuselage wallboard 1,
And the line direction of head and tail.
In addition, more specifically, it is excellent in of the invention in order to reserve enough spacing between fuselage wallboard 1 and type frame main body 2
The width for selecting the gap 5 is 100mm~500mm.
In the present invention, after dismantling positioning pin 43, the purpose is to allow loop bar 42 to rotate, and then make installing plate 45 and fuselage wall
Plate 1 staggers, it is allowed to fuselage wallboard 1 vertically move with it is vertically movable, while avoid interfering in moving process, collide.
More specifically, after positioning pin 43 are dismantled, loop bar 42 can also further be allowed in axially axial movement in set 44；Even it can also permit
Perhaps loop bar 42 is removed out of axial set 44, to realize the dismounting of loop bar 42；Corresponding installing plate 45 also will be with loop bar 42 together
It can be removable.Loop bar 42 so can further be avoided together with interference, resistance of the installing plate 45 to fuselage wallboard 1 in moving process
Hinder.
In addition, under normal circumstances, the main force transferring structure such as grid beam 3 is both provided with the inner side of fuselage wallboard 1.In the present invention
In, the installing plate 45 can be connected with the grid beam 3 of correspondence position；Pass through the connection of installing plate 45 and grid beam 3, realization pair
The supporting role of fuselage wallboard 1.Certainly, specifically, can be provided with installing plate 45 and in grid beam 3 and be bolted accordingly
Hole, the two is attached by bolt.
In addition, also providing a kind of removal method of fuselage wallboard of cross section radian more than π in the present invention, it uses above-mentioned
Cross section radian shown in the present invention is more than the fuselage wallboard assembly jig of π, after in fuselage wallboard 1, installation is complete, according to
Following steps carry out：
The first step：Prepare before removing：Supporting suspender is sling with row, suspender is connected and fixed with fuselage wallboard 1；
Remove the connection between fuselage wallboard 1 and installing plate 45；
Second step：Adjust 42 position of loop bar：Positioning pin 43 is removed, then rotating loop bar 42 makes installing plate 45 in fuselage wallboard
1 overall longitudinal direction staggers with fuselage wallboard 1；
3rd step：The entirety of fuselage wallboard 1 is moved up into certain distance L 1；
4th step：Fuselage wallboard 1 is overall to its heading translation certain distance L 2；
5th step：The entirety of fuselage wallboard 1 is sling upwards and is removed from assembly jig.
More specifically, in the third step, its displacement distance L1 is preferably 10mm；By displacement distance L1, the purpose is to will
Fuselage wallboard 1 is further separated with the supporting mechanism 2 of assembly jig, to avoid during follow-up removal fuselage wallboard 1 with
The supporting mechanism 4 of assembly jig produces friction, collision；In addition, in the 4th step, its displacement distance L2 is preferably 150mm；It is mobile
The purpose of distance L2 is, because the fuselage of head section usually has the characteristics that " pre-small post-large ", as shown in Figure 3；Utilize this
Feature, moves fuselage wallboard 1 by heading forward, the distance between siding and assembly jig can be made further to increase, and one
Determine to reduce further follow-up siding and the risk of assembly jig collision during removing fuselage wallboard 1 in degree；Meanwhile
The mounting base 41 on assembly jig can be caused to be located in the horizontal direction in fuselage wallboard 1 between adjacent two grid beam after movement greatly,
When this position relationship make it that subsequent step middle fuselage siding 1 moves upward out, siding from assembly jig upper mounting seat 41 resistance
Gear, and greatly reduce siding and the risk of assembly jig collision.
In addition, the present invention also further in the first step, while can tie down wall using more soft long ropes from all directions
Plate is simultaneously outwards drawn, and every rope is drawn by an operating personnel；By right in afterwards to 1 moving process of fuselage wallboard
The traction of rope is to reduce rocking for fuselage wallboard 1.
Claims (9)
1. cross section radian is more than the fuselage wallboard assembly jig of π, including may be disposed at fuselage wallboard (1) inside and be used for branch
Support the type frame main body (2) of fuselage wallboard (1), it is characterised in that：When assembling fuselage wallboard (1), outside the type frame main body (2)
Profile is to being reserved with certain interval (5) between fuselage wallboard；Supporting mechanism (4), the support are provided with the gap (5)
Mechanism (4) be installed on type frame main body (2) circumferential profile on, the supporting mechanism (4) include mounting base (41), loop bar (42) and
Positioning pin (43), mounting base (41) are fixedly installed in type frame main body (2), and axial set (44) is provided with mounting base (41),
The loop bar (42) is arranged in axial set (44), and loop bar (42) is installed by dismountable positioning pin (43), when
After dismantling positioning pin (43), the loop bar (42) can at least be freely rotated in axial set (44)；Set in one end of loop bar (42)
It is equipped with and is used to be connected with fuselage wallboard (1) with the installing plate (45) of loop bar (42) L-shaped distribution, the installing plate (45).
2. cross section radian as claimed in claim 1 is more than the fuselage wallboard assembly jig of π, it is characterised in that：Described
The width of gap (5) is 100mm~500mm.
3. cross section radian as claimed in claim 1 is more than the fuselage wallboard assembly jig of π, it is characterised in that：Work as dismounting
After positioning pin (43), the loop bar (42) is also axially movable in axial set (44).
4. cross section radian as claimed in claim 3 is more than the fuselage wallboard assembly jig of π, it is characterised in that：The set
Bar (42) is interior to be removably disposed in axial set (44).
5. the cross section radian stated such as claim 1 or 4 is more than the fuselage wallboard assembly jig of π, it is characterised in that：In fuselage
Grid beam (3) is provided with the inside of siding (1), the installing plate (45) is connected with the grid beam (3) of correspondence position.
6. the removal method of fuselage wallboard of the cross section radian more than π, using described in any one in the claims 1 to 5
Cross section radian be more than π fuselage wallboard assembly jig, after in fuselage wallboard (1), installation is complete, in accordance with the following steps into
OK：
The first step：Prepare before removing：Supporting suspender is sling with row, suspender is connected and fixed with fuselage wallboard (1)；Tear open
Except the connection between fuselage wallboard (1) and installing plate (45)；
Second step：Adjust loop bar (42) position：Positioning pin (43) is removed, then rotating loop bar (42) makes installing plate (45) in fuselage
The longitudinal direction of siding (1) entirety staggers with fuselage wallboard (1)；
3rd step：Fuselage wallboard (1) is integrally moved up into certain distance L 1；
4th step：Fuselage wallboard (1) is overall to its heading translation certain distance L 2；
5th step：Fuselage wallboard (1) is integrally sling upwards and is removed from assembly jig.
7. the removal method for fuselage wallboard of the cross section radian more than π as claimed in claim 6, it is characterised in that：
In 3rd step, its displacement distance L1 is 10mm；In the 4th step, its displacement distance L2 is 150mm.
8. the removal method for fuselage wallboard of the cross section radian more than π as claimed in claim 6, it is characterised in that：
In the first step, while siding is tied down from all directions using more soft long ropes and outwards drawn, and every rope is by one
Operating personnel draw；By the traction to rope to reduce fuselage wallboard (1) in afterwards to fuselage wallboard (1) moving process
Rock.
9. the removal method for being used for fuselage wallboard of the cross section radian more than π as described in any one in claim 6 to 8,
It is characterized in that：In second step, loop bar (42) is removed together with installing plate (45) after removing positioning pin (43).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711309994.5A CN108032052B (en) | 2017-12-11 | 2017-12-11 | Assembly jig for fuselage wall panel with radian of cross section larger than pi and moving-out method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711309994.5A CN108032052B (en) | 2017-12-11 | 2017-12-11 | Assembly jig for fuselage wall panel with radian of cross section larger than pi and moving-out method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108032052A true CN108032052A (en) | 2018-05-15 |
| CN108032052B CN108032052B (en) | 2019-12-24 |
Family
ID=62102229
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711309994.5A Active CN108032052B (en) | 2017-12-11 | 2017-12-11 | Assembly jig for fuselage wall panel with radian of cross section larger than pi and moving-out method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108032052B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11866201B2 (en) | 2022-05-03 | 2024-01-09 | The Boeing Company | Method and apparatus for the application of frame to fuselage pull-up force via fuselage skin waterline tensioning |
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| CN2555307Y (en) * | 2002-07-24 | 2003-06-11 | 陈旭昕 | Movable house |
| CN203061795U (en) * | 2013-01-28 | 2013-07-17 | 上海上飞飞机装备制造有限公司 | Wall board assembling jig |
| US8573282B2 (en) * | 2011-03-24 | 2013-11-05 | Macauto Industrial Co., Ltd. | Side bar device for a sunshade assembly |
| CN104309816A (en) * | 2014-10-29 | 2015-01-28 | 中航成飞民用飞机有限责任公司 | Method and tool for unloading wall panel assemblies at cargo space doors of airplanes |
| US20160354883A1 (en) * | 2013-07-08 | 2016-12-08 | The Boeing Company | Fuselage Stuffing Building and Feeder Lines |
| CN107161842A (en) * | 2017-05-27 | 2017-09-15 | 中航成飞民用飞机有限责任公司 | Barrel-shaped skinpiston group parts lift transporter |
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2017
- 2017-12-11 CN CN201711309994.5A patent/CN108032052B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2555307Y (en) * | 2002-07-24 | 2003-06-11 | 陈旭昕 | Movable house |
| US8573282B2 (en) * | 2011-03-24 | 2013-11-05 | Macauto Industrial Co., Ltd. | Side bar device for a sunshade assembly |
| CN203061795U (en) * | 2013-01-28 | 2013-07-17 | 上海上飞飞机装备制造有限公司 | Wall board assembling jig |
| US20160354883A1 (en) * | 2013-07-08 | 2016-12-08 | The Boeing Company | Fuselage Stuffing Building and Feeder Lines |
| CN104309816A (en) * | 2014-10-29 | 2015-01-28 | 中航成飞民用飞机有限责任公司 | Method and tool for unloading wall panel assemblies at cargo space doors of airplanes |
| CN107161842A (en) * | 2017-05-27 | 2017-09-15 | 中航成飞民用飞机有限责任公司 | Barrel-shaped skinpiston group parts lift transporter |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11866201B2 (en) | 2022-05-03 | 2024-01-09 | The Boeing Company | Method and apparatus for the application of frame to fuselage pull-up force via fuselage skin waterline tensioning |
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| Publication number | Publication date |
|---|---|
| CN108032052B (en) | 2019-12-24 |
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