CN219665741U - Quick positioning assembly fixture for wing body - Google Patents
Quick positioning assembly fixture for wing body Download PDFInfo
- Publication number
- CN219665741U CN219665741U CN202223394375.XU CN202223394375U CN219665741U CN 219665741 U CN219665741 U CN 219665741U CN 202223394375 U CN202223394375 U CN 202223394375U CN 219665741 U CN219665741 U CN 219665741U
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- CN
- China
- Prior art keywords
- positioning
- wing
- assembly
- fixture
- slide block
- 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
- 238000005553 drilling Methods 0.000 claims abstract description 25
- 230000006835 compression Effects 0.000 claims description 7
- 238000007906 compression Methods 0.000 claims description 7
- 238000000429 assembly Methods 0.000 claims description 5
- 230000000712 assembly Effects 0.000 claims description 4
- 238000003801 milling Methods 0.000 claims 1
- 230000007547 defect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
Classifications
-
- 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
Landscapes
- Earth Drilling (AREA)
Abstract
The utility model discloses a wing body rapid positioning assembly fixture which is reasonable in design, improves assembly accuracy and improves assembly efficiency. The positioning drilling fixture comprises a wing girder assembly part, a wing middle girder assembly part and a positioning drilling fixture, wherein the positioning drilling fixture comprises a fixture main body which is processed and formed by a processing center CNC, the fixture main body is connected with a positioning slide block I and a positioning slide block II, the positioning slide block I and the positioning slide block II are fastened and connected by screws, and the fixture main body and a drilling template with six diameters of 8 mm are fastened and connected by positioning pins and screws.
Description
Technical Field
The utility model relates to a rapid positioning assembly fixture, in particular to a rapid positioning assembly fixture for a wing body.
Background
In recent years, with the innovation of China and the substantial improvement of cultural living standard of people, light aircrafts as general aviation category are more and more in operation and flying in the aspects of travel, entertainment, advertising photography, cultural sports and the like, and great demand markets are formed in coastal, river-like, along-edge and economically developed areas. In the past, manufacturers producing light aircraft in China are few, and in recent years, the trend of the rapid increase exists, and the assembly of the wing fuselage of the existing light aircraft is to level the fuselage on the ground by using a metal bracket after the whole assembly is completed, then insert the assembled complete wing into the fuselage, further, the required dihedral angle of the wing is achieved, and then scribing, positioning and drilling are performed.
The assembly has the defects that the mutual assembly precision between the wing body sub-assemblies is poor, the left and right wing assembly references are not uniform, the sizes of products finished on a worker production line and design drawings have larger deviation, and the situation that the dihedral angle degree errors of the left and right wings are larger exists.
Disclosure of Invention
The utility model aims to solve the technical problem of overcoming the defects of the prior art and providing the rapid positioning assembly fixture for the wing body, which has reasonable design, improves the assembly precision and improves the assembly efficiency.
The technical scheme adopted by the utility model is as follows: the utility model provides a quick positioning assembly jig of wing fuselage, includes wing girder assembly part, wing center sill assembly part and location boring grab, location boring grab includes the anchor clamps main part through machining center CNC machine-shaping, connect location slider one and location slider two on the anchor clamps main part, with screw fastening connection, anchor clamps main part and a drilling template that has six diameters to be 8 millimeters utilize locating pin and screw fastening connection.
Further, the wing center sill assembly part is placed in the positioning drilling fixture, and the upper right-angle side of the wing center sill assembly part is in face-to-face close fit with the right-angle side of the positioning drilling fixture.
Further, after the wing girder assembly part is inserted into the wing middle girder assembly part, the wing girder assembly part is placed into the positioning drilling fixture, and the upper end face of the wing girder assembly part is ensured to be in close fit with the inclined face of the positioning drilling fixture.
Further, a second translational positioning sliding block is closely attached to the front end face of the wing middle beam assembly part along the sliding rail face, and a locking screw is locked for compressing and positioning.
Further, the assembly part of the translation wing girder is in close fit with the second positioning sliding block.
Further, the translational positioning sliding block is tightly attached to the lower end face of the wing girder assembly part, and is locked and positioned by the first compression screw.
Further, a positioning pin is utilized to assemble the drilling template to the positioning drilling fixture, and the drilling template is locked and fixed by a screw.
The beneficial effects of the utility model are as follows: because the unique reference of the positioning drilling fixture is utilized, the wing girder assembly part and the wing middle beam assembly part are subjected to drilling matching processing positioning under the same unchanged reference, and the accuracy and the consistency of the dihedral angle installation angles of the wing and the fuselage are accurately and efficiently ensured.
Drawings
Fig. 1 is a schematic structural view of the present utility model.
FIG. 2 is a schematic view of wing spar assembly and jig positioning.
FIG. 3 is a schematic illustration of wing center sill assembly and jig positioning.
Detailed Description
In the embodiment, as shown in fig. 1, the utility model comprises a wing girder assembly 1 and a wing middle girder assembly 3, a positioning drilling fixture 2 is arranged between the two assemblies, a positioning slide block I6 and a positioning slide block II 8 are arranged on the positioning drilling fixture 2, and the two positioning slide blocks are fixed by a compression screw.
In this embodiment, two groove steps which are CNC milled by a machining center are arranged in the positioning drilling fixture 2, the left groove step is placed in the wing girder assembly 1, the front end right angle surface of the wing girder assembly 1 is guaranteed to be in close fit with the right groove step right angle surface, the right groove step is placed in the wing center sill assembly 3, and the front end right angle surface of the wing center sill assembly 3 is guaranteed to be in close fit with the groove step right angle surface.
In this embodiment, the wing girder assembly 1 is positioned by means of a positioning slide block-6-surface collision surface, and is fixedly locked by using a first compression screw 7.
In the embodiment, the wing center sill assembly 3 is positioned by means of the second 8-face collision surface of the positioning sliding block, and is fixedly locked by using the second compression screw 9.
In the embodiment, the drilling template 4 is positioned on the positioning drilling fixture 2 through the positioning pin 5 and is pressed and fixed by a screw.
The utility model is applied to the technical field of aerospace.
While the embodiments of this utility model have been described in terms of practical aspects, they are not to be construed as limiting the meaning of this utility model, and modifications to the embodiments and combinations with other aspects thereof will be apparent to those skilled in the art from this description.
Claims (5)
1. A quick positioning assembly fixture for a wing body is characterized in that: the wing girder assembly comprises wing girder assemblies (1) and wing middle girder assemblies (3), wherein a positioning drilling fixture (2) is arranged between the two assemblies, a first positioning slide block (6) and a second positioning slide block (8) are arranged on the positioning drilling fixture (2), and the two positioning slide blocks are fixed by compression screws.
2. The rapid positioning assembly jig for a wing fuselage according to claim 1, wherein: two groove steps which are subjected to CNC milling by a machining center are arranged in the positioning drilling fixture (2), the wing girder assembly (1) is placed on the groove step on the left side, the front end right angle surface of the wing girder assembly (1) is guaranteed to be in close fit with the groove step right angle surface, the wing center sill assembly (3) is placed on the groove step on the right side, and the front end right angle surface of the wing center sill assembly (3) is guaranteed to be in close fit with the groove step right angle surface.
3. The rapid positioning assembly jig for a wing fuselage according to claim 2, wherein: the wing girder assembly (1) is positioned by means of the first (6) surface collision surface of the positioning slide block and is fixedly locked by using the first compression screw (7).
4. The rapid positioning assembly jig for a wing fuselage according to claim 2, wherein: the wing center sill assembly (3) is positioned by means of the surface collision surface of the positioning sliding block II (8), and is fixedly locked by using the second compression screw (9).
5. The rapid positioning assembly jig for a wing fuselage according to claim 1, wherein: the positioning drilling fixture (2) is provided with a drilling template (4) in a positioning way through a positioning pin (5) and is pressed and fixed by a screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223394375.XU CN219665741U (en) | 2022-12-19 | 2022-12-19 | Quick positioning assembly fixture for wing body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223394375.XU CN219665741U (en) | 2022-12-19 | 2022-12-19 | Quick positioning assembly fixture for wing body |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219665741U true CN219665741U (en) | 2023-09-12 |
Family
ID=87928076
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223394375.XU Active CN219665741U (en) | 2022-12-19 | 2022-12-19 | Quick positioning assembly fixture for wing body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219665741U (en) |
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2022
- 2022-12-19 CN CN202223394375.XU patent/CN219665741U/en active Active
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |